Federal Register / Vol. 86, No. 154 / Friday, August 13, 2021 / Proposed Rules 44663 

(5) For each fan vibration level reported, 

the fan hub serial number and hours time-inservice for this fan hub. 

(6) Installation date and service bulletin 

(SB) revision level for the installation of the 

bracket assembly with pad fuel flow meter 

and hose if installed before the effective date 

of this AD. 

(7) Any failures of the bracket assembly 

with pad fuel flow meter and hose installed 

in accordance with any SB listed in 

paragraph (h) or any prior revision of these 

SBs. 

(8) Installation date and SB revision level 

used for installation of the fuel control 

screws within the engine fuel control in 

accordance with Honeywell SB TFE731–73– 

5146 

(9) Any failures of fuel control screws after 

compliance with Honeywell SB TFE731–73– 

5146. 

(h) Replacement 

Within 12 months after the effective date 

of this AD or 750 hours time-in-service after 

the effective date of this AD, whichever 

occurs first, replace the engine fuel flow 

meter bracket in accordance with the 

Accomplishment Instructions, paragraphs 

3.A through 3.C, of the following Bombardier 

SB applicable to your airplane model. 

(1) Bombardier Learjet 40 SB 40–73–01, 

Revision 1, dated January 9, 2017. 

(2) Bombardier Learjet 45 SB 45–73–2 

Revision 1, dated January 9, 2017. 

(3) Bombardier Learjet 70 SB 70–73–01 

Revision 1, dated January 9, 2017. 

(4) Bombardier Learjet 75 SB 75–73–01, 

Revision 2, dated January 9, 2017. 

(i) Credit for Previous Actions 

(1) This paragraph provides credit for the 

actions required by paragraph (h) of this AD, 

if those actions were performed before the 

effective date of this AD using Bombardier 

Learjet 40 SB 40–73–01, Basic Issue, 

Bombardier Learjet 45 Service Bulletin SB 

45–73–2, Basic Issue, Bombardier Learjet 70 

SB 70–73–01, Basic Issue, or Bombardier 

Learjet 75 SB 75–73–01, Basic Issue, all dated 

October 3, 2016, or Bombardier Learjet 75 SB 

75–73–01, Revision 1, dated October 10, 

2016. 

(2) To take credit for any previous action, 

you must comply with paragraph (g) of this 

AD within 60 days after the effective date of 

this AD. 

(j) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Wichita ACO 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. 

(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 James Galstad, Aviation Safety 

Engineer, Wichita ACO Branch, FAA, 1801 S 

Airport Road, Wichita, KS 67209; phone: 

(316) 946–4135; email: james.galstad@

faa.gov or Wichita-COS@faa.gov; or Thomas 

Teplik, Aviation Safety Engineer, Wichita 

ACO Branch, FAA, 1801 S Airport Road, 

Wichita, KS 67209; phone: (316) 946–4196; 

email: thomas.teplik@faa.gov. 

(2) For service information identified in 

this AD, contact Learjet Inc., One Learjet 

Way, Wichita, KS, 67209; phone: (316) 946– 

2000; email: ac.ict@aero.bombardier.com; 

website: https:// 

businessaircraft.bombardier.com/en/aircraft/ 

Learjet.html. You may view this referenced 

service information at the FAA, 

Airworthiness Products Section, Operational 

Safety Branch, 901 Locust, Kansas City, MO 

64106. For information on the availability of 

this material at the FAA, call (816) 329–4148. 

Issued on August 5, 2021. 

Lance T. Gant, 

Director, Compliance & Airworthiness 

Division, Aircraft Certification Service. 

[FR Doc. 2021–17044 Filed 8–12–21; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2021–0663; Project 

Identifier MCAI–2020–01618–T] 

RIN 2120–AA64 

Airworthiness Directives; Airbus SAS 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: The FAA proposes to 

supersede Airworthiness Directive (AD) 

2016–17–12, which applies to all Airbus 

SAS Model A318 series airplanes; 

Model A319–111, –112, –113, –114, 

–115, –131, –132, and –133 airplanes; 

Model A320–211, –212, –214, –231, 

–232, and –233 airplanes; and Model 

A321–111, –112, –131, –211, –212, 

–213, –231, and –232 airplanes. AD 

2016–17–12 requires inspecting certain 

trimmable horizontal stabilizer actuators 

(THSAs) to determine the number of 

total flight cycles the THSA has 

accumulated, and replacing the THSA if 

necessary. Since the FAA issued AD 

2016–17–12, the FAA has determined 

that new or more restrictive 

airworthiness limitations are necessary. 

This proposed AD would require 

revising the existing maintenance or 

inspection program, as applicable, to 

incorporate new or more restrictive 

airworthiness limitations, as specified 

in a European Union Aviation Safety 

Agency (EASA) AD, which is proposed 

for incorporation by reference. The FAA 

is proposing this AD to address the 

unsafe condition on these products. 

DATES: The FAA must receive comments 

on this proposed AD by September 27, 

2021. 

ADDRESSES: You may send comments, 

using the procedures found in 14 CFR 

11.43 and 11.45, by any of the following 

methods: 

• Federal eRulemaking Portal: Go to 

https://www.regulations.gov. Follow the 

instructions for submitting comments. 

• Fax: 202–493–2251. 

• Mail: U.S. Department of 

Transportation, Docket Operations, 

M–30, West Building Ground Floor, 

Room W12–140, 1200 New Jersey 

Avenue SE, Washington, DC 20590. 

• Hand Delivery: Deliver to Mail 

address above between 9 a.m. and 5 

p.m., Monday through Friday, except 

Federal holidays. 

For EASA material that will be 

incorporated by reference (IBR) in this 

AD, contact EASA, Konrad-AdenauerUfer 3, 50668 Cologne, Germany; 

telephone +49 221 8999 000; email 

ADs@easa.europa.eu; internet 

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

IBR material on the EASA website at 

https://ad.easa.europa.eu. For Airbus 

service information identified in this 

proposed AD, contact Airbus SAS, 

Airworthiness Office—EIAS, RondPoint Emile Dewoitine No: 2, 31700 

Blagnac Cedex, France; telephone +33 5 

61 93 36 96; fax +33 5 61 93 44 51; email 

account.airworth-eas@airbus.com; 

internet https://www.airbus.com. 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–2021– 

0663. For the UTC Aerospace Systems 

material identified in this proposed AD 

that will not be incorporated by 

reference, contact Collins Aerospace, 

Product Support Department 13, 

Avenue de L’Eguillette—Saint-Ouen 

L’Aumone, Boite Postale 7186 95056 

Cergy Pontoise Cedex, France; 

telephone 1–877–808–7575; email crc@

collins.com; internet https://

www.collinsaerospace.com/support. 

Examining the AD Docket 

You may examine the AD docket on 

the internet at https:// 


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www.regulations.gov by searching for 

and locating Docket No. FAA–2021– 

0663; 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 NPRM, any 

comments received, and other 

information. The street address for 

Docket Operations is listed above. 

FOR FURTHER INFORMATION CONTACT: 

Sanjay Ralhan, Aerospace Engineer, 

Large Aircraft Section, International 

Validation Branch, FAA, 2200 South 

216th St., Des Moines, WA 98198; 

telephone and fax 206–231–3223; email 

sanjay.ralhan@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Comments Invited 

The FAA invites you to send any 

written relevant data, views, or 

arguments about this proposal. Send 

your comments to an address listed 

under ADDRESSES. Include ‘‘Docket No. 

FAA–2021–0663; Project Identifier 

MCAI–2020–01618–T’’ at the beginning 

of your comments. The most helpful 

comments reference a specific portion of 

the proposal, explain the reason for any 

recommended change, and include 

supporting data. The FAA will consider 

all comments received by the closing 

date and may amend the proposal 

because of those comments. 

Except for Confidential Business 

Information (CBI) as described in the 

following paragraph, and other 

information as described in 14 CFR 

11.35, the FAA will post all comments 

received, without change, to https://

www.regulations.gov, including any 

personal information you provide. The 

agency will also post a report 

summarizing each substantive verbal 

contact received about this proposed 

AD. 

Confidential Business Information 

CBI is commercial or financial 

information that is both customarily and 

actually treated as private by its owner. 

Under the Freedom of Information Act 

(FOIA) (5 U.S.C. 552), CBI is exempt 

from public disclosure. If your 

comments responsive to this NPRM 

contain commercial or financial 

information that is customarily treated 

as private, that you actually treat as 

private, and that is relevant or 

responsive to this NPRM, it is important 

that you clearly designate the submitted 

comments as CBI. Please mark each 

page of your submission containing CBI 

as ‘‘PROPIN.’’ The FAA will treat such 

marked submissions as confidential 

under the FOIA, and they will not be 

placed in the public docket of this 

NPRM. Submissions containing CBI 

should be sent to Sanjay Ralhan, 

Aerospace Engineer, Large Aircraft 

Section, International Validation 

Branch, FAA, 2200 South 216th St., Des 

Moines, WA 98198; telephone and fax 

206–231–3223; email sanjay.ralhan@

faa.gov. Any commentary that the FAA 

receives which is not specifically 

designated as CBI will be placed in the 

public docket for this rulemaking. 

Background 

The FAA issued AD 2016–17–12, 

Amendment 39–18625 (81 FR 58823, 

August 26, 2016) (AD 2016–17–12), for 

all Airbus SAS Model A318 series 

airplanes; Model A319–111, –112, –113, 

–114, –115, –131, –132, and –133 

airplanes; Model A320–211, –212, –214, 

–231, –232, and –233 airplanes; and 

Model A321–111, –112, –131, –211, 

–212, –213, –231, and –232 airplanes. 

AD 2016–17–12 requires inspecting 

certain THSAs to determine the number 

of total flight cycles the THSA has 

accumulated, and replacing the THSA if 

necessary. The FAA issued AD 2016– 

17–12 to address premature wear of the 

carbon friction disks on the no-back 

brake (NBB) of the THSA, which could 

lead to reduced braking efficiency in 

certain load conditions, and, in 

conjunction with the inability of the 

power gear train to keep the ball screw 

in its last commanded position, could 

result in uncommanded movements of 

the trimmable horizontal stabilizer and 

loss of control of the airplane. 

Actions Since AD 2016–17–12 Was 

Issued 

Since the FAA issued AD 2016–17– 

12, new investigations determined that 

the compliance time for removal from 

service and replacement of certain 

THSA NBB disks must be reduced. This 

task was required by AD 2016–17–12, 

and the task and newly reduced 

compliance time have now been 

incorporated into Airbus A318/A319/ 

A320/A321 Airworthiness Limitations 

Section (ALS) Part 4 Variation 7.1, dated 

October 5, 2020. The FAA has therefore 

determined that new or more restrictive 

airworthiness limitations are necessary. 

EASA, which is the Technical Agent 

for the Member States of the European 

Union, has issued EASA AD 2020–0270, 

dated December 7, 2020 (EASA AD 

2020–0270) (also referred to as the 

Mandatory Continuing Airworthiness 

Information, or the MCAI), to correct an 

unsafe condition for all Airbus SAS 

Model A318–111, –112, –121, and –122 

airplanes; Model A319–111, –112, –113, 

–114, –115, –131, –132, –133, –151N, 

–153N, and –171N airplanes; Model 

A320–211, –212, –214, –216, –231, 

–232, –233, –251N, –252N, –253N, 

–271N, –272N, and –273N airplanes; 

and Model A321–111, –112, –131, –211, 

–212, –213, –231, –232, –251N, –251NX, 

–252N, –252NX, –253N, –253NX, 

–271N, –271NX, –272N, and –272NX 

airplanes. Model A320–215 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. 

Airplanes with an original 

airworthiness certificate or original 

export certificate of airworthiness 

issued after October 5, 2020, must 

comply with the airworthiness 

limitations specified as part of the 

approved type design and referenced on 

the type certificate data sheet. However, 

Airbus A318/A319/A320/A321 

Airworthiness Limitations Section 

(ALS) Part 4 Variation 7.1 specifies that 

replacements can be accomplished in 

accordance with certain service 

information, while this proposed AD 

would require accomplishing those 

replacements in accordance with certain 

service information. To ensure all 

maintenance or inspection programs 

incorporate the revised task, including 

the revised replacement requirements, 

this proposed AD would therefore 

require all operators to revise their 

existing maintenance or inspection 

program to include either the revised 

task including the revised provisions for 

replacement, or the revised provisions 

for replacement, depending on when the 

original airworthiness certificate or 

original export certificate of 

airworthiness was issued. 

EASA AD 2020–0270 specifies that it 

requires a task (limitation) already 

required by EASA AD 2020–0034, dated 

February 25, 2020 (which corresponds 

to FAA AD 2020–21–10, Amendment 

39–21283 (85 FR 65190, October 15, 

2020) (AD 2020–21–10)) and invalidates 

(terminates) prior instructions for that 

task. This proposed AD would terminate 

the ALS limitation for task 274000– 

00004–1–E for the THSAs, as required 

by paragraph (i) of AD 2020–21–10, for 

Model A318–111, –112, –121, and –122 

airplanes; Model A319–111, –112, –113, 

–114, –115, –131, –132, –133, –151N, 

and –153N airplanes; Model A320–211, 

–212, –214, –216, –231, –232, –233, 

–251N, –252N, –253N, –271N, –272N, 

and –273N airplanes; and Model A321– 

111, –112, –131, –211, –212, –213, –231, 

–232, –251N, –251NX, –252N, –252NX, 

–253N, –253NX, –271N, –271NX, 

–272N, and –272NX airplanes; with an 

original airworthiness certificate or 

original export certificate of 

airworthiness issued on or before 

November 7, 2019, only. 


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This proposed AD was prompted by 

a determination that new or more 

restrictive airworthiness limitations are 

necessary. The FAA is proposing this 

AD to address premature wear of the 

carbon friction disks on the NBB of the 

THSA, which could lead to reduced 

braking efficiency in certain load 

conditions, and, in conjunction with the 

inability of the power gear train to keep 

the ball screw in its last commanded 

position, could result in uncommanded 

movements of the trimmable horizontal 

stabilizer and loss of control of the 

airplane. See the MCAI for additional 

background information. 

Model A320–216 Airplanes 

The Airbus SAS Model A320–216 was 

U.S. type certificated on December 19, 

2016. Before that date, any EASA ADs 

that affected Model A320–216 airplanes 

were included in the U.S. type 

certificate as part of the Required 

Airworthiness Actions List (RAAL). One 

or more Model A320–216 airplanes have 

subsequently been placed on the U.S. 

Register, and will now be included in 

FAA AD actions. For Model A320–216 

airplanes, the requirements that 

correspond to AD 2016–17–12 were 

mandated by the MCAI via the RAAL. 

Although that RAAL requirement is still 

in effect, for continuity and clarity the 

FAA has identified Model A320–216 

airplanes in paragraph (c) of this 

proposed AD; the MCAI that is specified 

in paragraph (l) in this proposed AD 

includes restated requirements, which 

would therefore apply to those 

airplanes. 

Related Service Information Under 1 

CFR Part 51 

EASA AD 2020–0270 describes new 

or more restrictive airworthiness 

limitations for airplane structures and 

safe life limits. 

Airbus A318/A319/A320/A321 

Airworthiness Limitations Section 

(ALS) Part 4 Variation 7.1, dated 

October 5, 2020, describes a task for 

removal from service and replacement 

of certain THSA NBB disks. 

This proposed AD would also require 

Airbus Service Bulletin A320–27–1242, 

Revision 01, dated February 4, 2016, 

which the Director of the Federal 

Register approved for incorporation by 

reference as of September 30, 2016 (81 

FR 58823, August 26, 2016). 

This material is reasonably available 

because the interested parties have 

access to it through their normal course 

of business or by the means identified 

in the ADDRESSES section. 

FAA’s Determination and Requirements 

of This Proposed AD 

This product has been approved by 

the aviation authority of another 

country, and is approved for operation 

in the United States. Pursuant to the 

FAA’s bilateral agreement with the State 

of Design Authority, the FAA has been 

notified of the unsafe condition 

described in the MCAI and service 

information referenced above. The FAA 

is proposing this AD because the FAA 

has evaluated all pertinent information 

and determined an unsafe condition 

exists and is likely to exist or develop 

on other products of the same type 

design. 

Proposed AD Requirements 

This proposed AD would retain the 

requirements of AD 2016–17–12. This 

proposed AD would also require 

revising the existing maintenance or 

inspection program, as applicable, to 

incorporate new or more restrictive 

airworthiness limitations, which are 

specified in EASA AD 2020–0270 

described previously, as proposed for 

incorporation by reference. Any 

differences with EASA AD 2020–0270 

are identified as exceptions in the 

regulatory text of this AD. 

This proposed AD would require 

revisions to certain operator 

maintenance documents to include new 

actions (e.g., inspections). Compliance 

with these actions is required by 14 CFR 

91.403(c). For airplanes that have been 

previously modified, altered, or repaired 

in the areas addressed by this proposed 

AD, the operator may not be able to 

accomplish the actions described in the 

revisions. In this situation, to comply 

with 14 CFR 91.403(c), the operator 

must request approval for an alternative 

method of compliance according to 

paragraph (p)(1) of this proposed AD. 

Explanation of Required Compliance 

Information 

In the FAA’s ongoing efforts to 

improve the efficiency of the AD 

process, the FAA developed a process to 

use certain civil aviation authority 

(CAA) ADs as the primary source of 

information for compliance with 

requirements for corresponding FAA 

ADs. The FAA has been coordinating 

this process with manufacturers and 

CAAs. As a result, the FAA proposes to 

incorporate EASA AD 2020–0270 by 

reference in the FAA final rule. This 

proposed AD would, therefore, require 

compliance with EASA AD 2020–0270 

in its entirety through that 

incorporation, except for any differences 

identified as exceptions in the 

regulatory text of this proposed AD. 

Using common terms that are the same 

as the heading of a particular section in 

EASA AD 2020–0270 does not mean 

that operators need comply only with 

that section. For example, where the AD 

requirement refers to ‘‘all required 

actions and compliance times,’’ 

compliance with this AD requirement is 

not limited to the section titled 

‘‘Required Action(s) and Compliance 

Time(s)’’ in EASA AD 2020–0270. 

Service information required by EASA 

AD 2020–0270 for compliance will be 

available at https://www.regulations.gov 

by searching for and locating Docket No. 

FAA–2021–0663 after the FAA final 

rule is published. 

Airworthiness Limitation ADs Using 

the New Process 

The FAA’s process of incorporating 

by reference MCAI ADs as the primary 

source of information for compliance 

with corresponding FAA ADs has been 

limited to certain MCAI ADs (primarily 

those with service bulletins as the 

primary source of information for 

accomplishing the actions required by 

the FAA AD). However, the FAA is now 

expanding the process to include MCAI 

ADs that require a change to 

airworthiness limitation documents, 

such as airworthiness limitation 

sections. 

For these ADs that incorporate by 

reference an MCAI AD that changes 

airworthiness limitations, the FAA 

requirements are unchanged. Operators 

must revise the existing maintenance or 

inspection program, as applicable, to 

incorporate the information specified in 

the new airworthiness limitation 

document. The airworthiness 

limitations must be followed according 

to 14 CFR 91.403(c) and 91.409(e). 

The previous format of the 

airworthiness limitation ADs included a 

paragraph that specified that no 

alternative actions (e.g., inspections) or 

intervals may be used unless the actions 

or intervals are approved as an 

alternative method of compliance 

(AMOC) in accordance with the 

procedures specified in the AMOCs 

paragraph under ‘‘Other FAA 

Provisions.’’ This new format includes a 

‘‘New Provisions for Alternative Actions 

and Intervals’’ paragraph that does not 

specifically refer to AMOCs, but 

operators may still request an AMOC to 

use an alternative actions or intervals. 

Costs of Compliance 

The FAA estimates that this proposed 

AD affects 1,630 airplanes of U.S. 

registry. The FAA estimates the 

following costs to comply with this 

proposed AD: 


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ESTIMATED COSTS FOR REQUIRED ACTIONS * 

Action Labor cost Parts cost Cost per 

product 

Cost on U.S. 

operators 

Retained actions from AD 2016–17–12 (959 airplanes) 1 work-hour × $85 per hour = $85 .. $0 $85 $81,515 

* Table does not include estimated costs for reporting/revising the existing maintenance or inspection program. 

The FAA has determined that revising 

the existing maintenance or inspection 

program takes an average of 90 workhours per operator, although the agency 

recognizes that this number may vary 

from operator to operator. Since 

operators incorporate maintenance or 

inspection program changes for their 

affected fleet(s), the FAA has 

determined that a per-operator estimate 

is more accurate than a per-airplane 

estimate. 

The FAA estimates the total cost per 

operator for the new proposed actions to 

be $7,650 (90 work-hours × $85 per 

work-hour). 

The FAA estimates the following 

costs to do any necessary on-condition 

actions that would be required based on 

the results of any required actions. The 

FAA has no way of determining the 

number of aircraft that might need this 

on-condition action: 

ESTIMATED COSTS OF ON-CONDITION ACTIONS

Labor cost Parts cost Cost per 

product 

21 work-hours × $85 per hour = $1,785 ................................................................................................................. $26,500 $28,285 

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 determined that this 

proposed AD would not have federalism 

implications under Executive Order 

13132. This proposed AD would 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 this proposed regulation: 

(1) Is not a ‘‘significant regulatory 

action’’ under Executive Order 12866, 

(2) Would not affect intrastate 

aviation in Alaska, and 

(3) Would 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 Proposed Amendment 

Accordingly, under the authority 

delegated to me by the Administrator, 

the FAA proposes to amend 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) 2016–17–12, Amendment 39– 

18625 (81 FR 58823, August 26, 2016); 

and 

■ b. Adding the following new AD: 

Airbus SAS: Docket No. FAA–2021–0663; 

Project Identifier MCAI–2020–01618–T. 

(a) Comments Due Date 

The FAA must receive comments on this 

airworthiness directive (AD) by September 

27, 2021. 

(b) Affected ADs 

(1) This AD replaces AD 2016–17–12, 

Amendment 39–18625 (81 FR 58823, August 

26, 2016) (AD 2016–17–12). 

(2) This AD affects AD 2020–21–10, 

Amendment 39–21283 (85 FR 65190, October 

15, 2020) (AD 2020–21–10). 

(c) Applicability 

This AD applies to all Airbus SAS 

airplanes, certificated in any category, 

identified in paragraphs (c)(1) through (7) of 

this AD. 

(1) Model A318–111, –112, –121, and –122 

airplanes. 

(2) Model A319–111, –112, –113, –114, 

–115, –131, –132, and –133 airplanes. 

(3) Model A320–211, –212, –214, –216, 

–231, –232, and –233 airplanes. 

(4) Model A321–111, –112, –131, –211, 

–212, –213, –231, and –232 airplanes. 

(5) Model A319–151N, –153N, and –171N 

airplanes. 

(6) Model A320–251N, –252N, –253N, 

–271N, –272N, and –273N airplanes. 

(7) Model A321–251N, –251NX, –252N, 

–252NX, –253N, –253NX, –271N, –271NX, 

–272N, and –272NX airplanes. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 05, Time Limits/Maintenance 

Checks; 27, Flight Controls. 

(e) Reason 

This AD was prompted by a determination 

that new or more restrictive airworthiness 

limitations are necessary. The FAA is issuing 

this AD to address premature wear of the 

carbon friction disks on the no-back brake 

(NBB) of the trimmable horizontal stabilizer 

actuator (THSA), which could lead to 

reduced braking efficiency in certain load 

conditions, and, in conjunction with the 

inability of the power gear train to keep the 

ball screw in its last commanded position, 

could result in uncommanded movements of 

the trimmable horizontal stabilizer and loss 

of control of the airplane. 


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Federal Register / Vol. 86, No. 154 / Friday, August 13, 2021 / Proposed Rules 44667 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Retained Inspection To Determine THSA 

Part Number and Accumulated Total Flight 

Cycles, With No Changes 

This paragraph restates the requirements of 

paragraph (g) of AD 2016–17–12, with no 

changes. For airplanes identified in 

paragraphs (c)(1) through (4) of this AD: No 

later than each date specified in paragraphs 

(g)(1) through (5) of this AD, inspect the 

THSA to determine if it has a part number 

(P/N) 47145–(XXX), and, if any THSA P/N 

47145–(XXX) is found, determine the total 

number of flight cycles accumulated since 

the THSA’s first installation on an airplane, 

or since the most recent NBB replacement, 

whichever is later. A review of airplane 

delivery or maintenance records is acceptable 

in lieu of this inspection if the part number 

of the THSA can be conclusively determined 

from that review. In case maintenance 

records concerning the most recent NBB disk 

replacement are unavailable or incomplete, 

the total flight cycles accumulated since first 

installation of the THSA on an airplane 

apply. Accomplishing the maintenance or 

inspection program revision required by 

paragraph (l) of this AD terminates the 

requirements of this paragraph. 

(1) As of September 30, 2016 (the effective 

date of AD 2016–17–12): The THSA flightcycle limit (since first installation on an 

airplane, or since the most recent NBB 

replacement, whichever is later) is 40,000 

total flight cycles. 

(2) As of December 31, 2016: The THSA 

flight-cycle limit (since first installation on 

an airplane, or since the most recent NBB 

replacement, whichever is later) is 36,000 

total flight cycles. 

(3) As of December 31, 2017: The THSA 

flight-cycle limit (since first installation on 

an airplane, or since the most recent NBB 

replacement, whichever is later) is 33,600 

total flight cycles. 

(4) As of December 31, 2018: The THSA 

flight-cycle limit (since first installation on 

an airplane, or since the most recent NBB 

replacement, whichever is later) is 31,600 

total flight cycles. 

(5) As of December 31, 2019: The THSA 

flight-cycle limit (since first installation on 

an airplane, or since the most recent NBB 

replacement, whichever is later) is 30,000 

total flight cycles. 

(h) Retained Replacements, With No 

Changes 

This paragraph restates the requirements of 

paragraph (h) of AD 2016–17–12, with no 

changes. For airplanes identified in 

paragraphs (c)(1) through (4) of this AD: For 

airplanes with any THSA P/N 47145–(XXX), 

do the replacements required by paragraphs 

(h)(1) and (2) of this AD. Accomplishing the 

maintenance or inspection program revision 

required by paragraph (l) of this AD 

terminates the requirements of this 

paragraph. 

(1) No later than each date specified in 

paragraphs (g)(1) through (5) of this AD, 

replace all THSA that have reached or 

exceeded on each date the corresponding 

number of flight cycles specified in 

paragraphs (g)(1) through (5) of this AD. Do 

the replacement in accordance with the 

Accomplishment Instructions of Airbus 

Service Bulletin A320–27–1242, Revision 01, 

dated February 4, 2016. Affected THSAs 

must be replaced with serviceable THSAs. 

(2) As of each date specified in paragraphs 

(g)(1) through (5) of this AD, and before 

exceeding the flight cycle limit 

corresponding to each date, as applicable: 

Replace each THSA with a serviceable 

THSA, in accordance with the 

Accomplishment Instructions of Airbus 

Service Bulletin A320–27–1242, Revision 01, 

dated February 4, 2016. 

(i) Retained Definition of Serviceable THSA, 

With No Changes 

This paragraph restates the definition of 

paragraph (i) of AD 2016–17–12, with no 

changes. For airplanes identified in 

paragraphs (c)(1) through (4) of this AD: For 

the purposes of this AD, a serviceable THSA 

is a THSA that has not exceeded the 

applicable flight-cycle limits, as specified 

paragraphs (g)(1) through (5) of this AD, since 

first installation of the THSA on an airplane 

or since last NBB replacement, whichever is 

later. 

Note 1 to paragraph (i): Guidance for NBB 

disk replacement can be found in UTC 

Aerospace Systems Service Bulletin 47145– 

27–17, Revision 1, dated July 21, 2015. 

(j) Retained Parts Installation Limitation, 

With No Changes 

This paragraph restates the provisions of 

paragraph (j) of AD 2016–17–12, with no 

changes. For airplanes identified in 

paragraphs (c)(1) through (4) of this AD: As 

of each date specified in paragraphs (g)(1) 

through (5) of this AD, as applicable, only 

installation of a serviceable THSA P/N 

47145–(XXX) is allowed on an airplane. 

Accomplishing the maintenance or 

inspection program revision required by 

paragraph (l) of this AD terminates the 

requirements of this paragraph. 

(k) Retained Credit for Previous Actions, 

With No Changes 

This paragraph restates the requirements of 

paragraph (k) of AD 2016–17–12, with no 

changes. For airplanes identified in 

paragraphs (c)(1) through (4) of this AD: This 

paragraph provides credit for actions 

required by paragraph (h) of this AD, if those 

actions were performed before September 30, 

2016 (the effective date of AD 2016–17–12), 

using Airbus Service Bulletin A320–27–1242, 

dated February 9, 2015. 

(l) New Maintenance or Inspection Program 

Revision 

(1) For the airplanes identified in 

paragraph (c) of this AD with an original 

airworthiness certificate or original export 

certificate of airworthiness issued on or 

before October 5, 2020, except as specified in 

paragraph (m) of this AD: Comply with all 

required actions and compliance times 

specified in, and in accordance with, 

European Union Aviation Safety Agency 

(EASA) AD 2020–0270, dated December 7, 

2020 (EASA AD 2020–0270). Accomplishing 

the maintenance or inspection program 

revision required by this paragraph 

terminates the requirements of paragraphs 

(g), (h), and (j) of this AD. 

(2) For the airplanes identified in 

paragraph (c) of this AD with an original 

airworthiness certificate or original export 

certificate of airworthiness issued after 

October 5, 2020, revise the existing 

maintenance or inspection program, as 

applicable, to incorporate the provision 

specified in paragraph (m)(7) of this AD. 

(m) Exceptions to EASA AD 2020–0270 

(1) Where EASA AD 2020–0270 refers to its 

effective date, this AD requires using the 

effective date of this AD. 

(2) The requirements specified in 

paragraphs (1) and (2) of EASA AD 2020– 

0270 do not apply to this AD. 

(3) Paragraph (3) of EASA AD 2020–0270 

specifies revising ‘‘the approved AMP’’ 

within 12 months after its effective date, but 

this AD requires revising the existing 

maintenance or inspection program, as 

applicable, within 90 days after the effective 

date of this AD. 

(4) The initial compliance time for doing 

the tasks specified in paragraph (3) of EASA 

AD 2020–0270 is at the applicable 

‘‘thresholds’’ as incorporated by the 

requirements of paragraph (3) of EASA AD 

2020–0270, or within 90 days after the 

effective date of this AD, whichever occurs 

later. 

(5) The provisions specified in paragraph 

(4) of EASA AD 2020–0270 do not apply to 

this AD. 

(6) The ‘‘Remarks’’ section of EASA AD 

2020–0270 does not apply to this AD. 

(7) For all airplanes identified in paragraph 

(c) of this AD: Where Note 1 in the service 

information referenced in EASA AD 2020– 

0270 specifies ‘‘NBB carbon disc replacement 

can be accomplished in accordance with SB 

A320–27–1242 or VSB 47145–27–17,’’ for 

this AD use ‘‘NBB carbon disk replacement 

must be accomplished in accordance with SB 

A320–27–1242.’’ 

(n) New Provisions for Alternative Actions 

and Intervals 

After the existing maintenance or 

inspection program has been revised as 

required by paragraph (l) of this AD, no 

alternative actions (e.g., inspections) or 

intervals are allowed unless they are 

approved as specified in the provisions of the 

‘‘Ref. Publications’’ section of EASA AD 

2020–0270. 

(o) Terminating Action for Certain 

Requirements of AD 2020–21–10 

Accomplishing the actions required by this 

AD terminates the ALS limitation task 

274000–00004–1–E for the THSA, as required 

by paragraph (i) of AD 2020–21–10, for 

Model A318–111, –112, –121, and –122 

airplanes; Model A319–111, –112, –113, 

–114, –115, –131, –132, –133, –151N, and 

–153N airplanes; Model A320–211, –212, 

–214, –216, –231, –232, –233, –251N, –252N, 

–253N, –271N, –272N, and –273N airplanes; 

and Model A321–111, –112, –131, –211, 

–212, –213, –231, –232, –251N, –251NX, 

–252N, –252NX, –253N, –253NX, –271N, 


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44668 Federal Register / Vol. 86, No. 154 / Friday, August 13, 2021 / Proposed Rules 

–271NX, –272N, and –272NX airplanes; with 

an original airworthiness certificate or 

original export certificate of airworthiness 

issued on or before November 7, 2019, only. 

(p) Other FAA AD Provisions 

The following provisions also apply to this 

AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, Large Aircraft 

Section, International Validation Branch, 

FAA, has the authority to approve AMOCs 

for this AD, if requested using the procedures 

found in 14 CFR 39.19. In accordance with 

14 CFR 39.19, send your request to your 

principal inspector or responsible Flight 

Standards Office, as appropriate. If sending 

information directly to the Large Aircraft 

Section, International Validation Branch, 

send it to the attention of the person 

identified in paragraph (q)(4) of this AD. 

Information may be emailed to: 9-AVS-AIR730-AMOC@faa.gov. 

(i) Before using any approved AMOC, 

notify your appropriate principal inspector, 

or lacking a principal inspector, the manager 

of the responsible Flight Standards Office. 

(ii) AMOCs approved previously for AD 

2016–17–12 are approved as AMOCs for the 

corresponding provisions of EASA AD 2020– 

0270 that are required by paragraph (l) of this 

AD. 

(2) Contacting the Manufacturer: For any 

requirement in this AD to obtain instructions 

from a manufacturer, the instructions must 

be accomplished using a method approved 

by the Manager, Large Aircraft Section, 

International Validation Branch, FAA; or 

EASA; or Airbus SAS’s EASA Design 

Organization Approval (DOA). If approved by 

the DOA, the approval must include the 

DOA-authorized signature. 

(3) Required for Compliance (RC): Except 

as required by paragraph (p)(2) of this AD, if 

any service information contains procedures 

or tests that are identified as RC, those 

procedures and tests must be done to comply 

with this AD; any procedures or tests that are 

not identified as RC are recommended. Those 

procedures and tests that are not identified 

as RC may be deviated from using accepted 

methods in accordance with the operator’s 

maintenance or inspection program without 

obtaining approval of an AMOC, provided 

the procedures and tests identified as RC can 

be done and the airplane can be put back in 

an airworthy condition. Any substitutions or 

changes to procedures or tests identified as 

RC require approval of an AMOC. 

(q) Related Information 

(1) For EASA AD 2020–0270, contact 

EASA, Konrad-Adenauer-Ufer 3, 50668 

Cologne, Germany; telephone +49 221 8999 

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

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

EASA AD on the EASA website at https://

ad.easa.europa.eu. 

(2) For Airbus service information 

identified in this proposed AD, contact 

Airbus SAS, Airworthiness Office—EIAS, 

Rond-Point Emile Dewoitine No: 2, 31700 

Blagnac Cedex, France; telephone +33 5 61 

93 36 96; fax +33 5 61 93 44 51; email 

account.airworth-eas@airbus.com; internet 

https://www.airbus.com. 

(3) For UTC Aerospace Systems material 

identified in this proposed AD, contact 

Collins Aerospace, Product Support 

Department 13, Avenue de L’Eguillette— 

Saint-Ouen L’Aumone, Boite Postale 7186 

95056 Cergy Pontoise Cedex, France; 

telephone 1–877–808–7575; email crc@

collins.com; internet https://

www.collinsaerospace.com/support. 

(4) You may view this material at the FAA, 

Airworthiness Products Section, Operational 

Safety Branch, 2200 South 216th St., Des 

Moines, WA. For information on the 

availability of this material at the FAA, call 

206–231–3195. 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–2021–0663. 

(5) For more information about this AD, 

contact Sanjay Ralhan, Aerospace Engineer, 

Large Aircraft Section, International 

Validation Branch, FAA, 2200 South 216th 

St., Des Moines, WA 98198; telephone and 

fax 206–231–3223; email sanjay.ralhan@

faa.gov. 

Issued on August 5, 2021. 

Lance T. Gant, 

Director, Compliance & Airworthiness 

Division, Aircraft Certification Service. 

[FR Doc. 2021–17091 Filed 8–12–21; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 71 

[Docket No. FAA–2021–0637; Airspace 

Docket No. 21–ANM–31] 

RIN 2120–AA66 

Proposed Establishment Class E 

Airspace; Portland-Troutdale Airport, 

OR 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: This action proposes to 

establish Class E airspace, designated as 

an extension to a Class D or Class E 

surface area, at Portland-Troutdale 

Airport, Portland, OR. This action also 

proposes numerous administrative 

updates to the Class D and Class E2 text 

headers and airspace descriptions. This 

action would ensure the safety and 

management of instrument flight rules 

(IFR) operations at the airport. 

DATES: Comments must be received on 

or before September 27, 2021. 

ADDRESSES: Send comments on this 

proposal to the U.S. Department of 

Transportation, Docket Operations, 1200 

New Jersey Avenue SE, West Building 

Ground Floor, Room W12–140, 

Washington, DC 20590; telephone: 1– 

800–647–5527, or (202) 366–9826. You 

must identify FAA Docket No. FAA– 

2021–0637; Airspace Docket No. 21– 

ANM–31, at the beginning of your 

comments. You may also submit 

comments through the internet at 

https://www.regulations.gov. 

FAA Order 7400.11E, Airspace 

Designations and Reporting Points, and 

subsequent amendments can be viewed 

online at https://www.faa.gov/air_

traffic/publications/. For further 

information, you can contact the 

Airspace Policy Group, Federal Aviation 

Administration, 800 Independence 

Avenue SW, Washington, DC 20591; 

telephone: (202) 267–8783. The Order is 

also available for inspection at the 

National Archives and Records 

Administration (NARA). For 

information on the availability of FAA 

Order 7400.11E at NARA, email 

fr.inspection@nara.gov or go to https:// 

www.archives.gov/federal-register/cfr/ 

ibr-locations.html. 

FOR FURTHER INFORMATION CONTACT: 

Matthew Van Der Wal, Federal Aviation 

Administration, Western Service Center, 

Operations Support Group, 2200 S. 

216th Street, Des Moines, WA 98198; 

telephone (206) 231–3695. 

SUPPLEMENTARY INFORMATION: 

Authority for This Rulemaking 

The FAA’s authority to issue rules 

regarding aviation safety is found in 

Title 49 of the United States Code. 

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. This rulemaking is 

promulgated under the authority 

described in Subtitle VII, Part A, 

Subpart I, Section 40103. Under that 

section, the FAA is charged with 

prescribing regulations to assign the use 

of airspace necessary to ensure the 

safety of aircraft and the efficient use of 

airspace. This regulation is within the 

scope of that authority, as it would 

establish Class E airspace at PortlandTroutdale Airport, Portland, OR, to 

support IFR operations at the airport. 

Comments Invited 

Interested parties are invited to 

participate in this proposed rulemaking 

by submitting such written data, views, 

or arguments, as they may desire. 

Comments that provide the factual basis 

supporting the views and suggestions 

presented are particularly helpful in 

developing reasoned regulatory 

decisions on the proposal. Comments 

are specifically invited on the overall 

regulatory, aeronautical, economic, 

environmental, and energy-related 


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