Federal Register / Vol. 86, No. 43 / Monday, March 8, 2021 / Proposed Rules 13237 

Rotorcraft Section, send it to: Manager, 

Strategic Policy Rotorcraft Section, FAA, 

10101 Hillwood Pkwy., Fort Worth, TX 

76177; telephone 817–222–5110. Information 

may be emailed to: 9-ASW-FTW-AMOCRequests@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 EASA AD 2020–0084, 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. You may view this 

material 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–2021–0104. 

(2) For more information about this AD, 

contact Hal Jensen, Aerospace Engineer, 

Operational Safety Branch, FAA, 470 

L’Enfant Plaza SW, Washington, DC 20024; 

telephone 202–267–9167; email hal.jensen@

faa.gov. 

Issued on February 19, 2021. 

Lance T. Gant, 

Director, Compliance & Airworthiness 

Division, Aircraft Certification Service. 

[FR Doc. 2021–04185 Filed 3–5–21; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2019–0113; Product 

Identifier 2017–SW–140–AD] 

RIN 2120–AA64 

Airworthiness Directives; Airbus 

Helicopters Deutschland GmbH 

Helicopters 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: The FAA proposes to 

supersede Airworthiness Directive (AD) 

2016–11–21 for Airbus Helicopters 

Deutschland GmbH (Airbus Helicopters) 

Model EC135P1, EC135P2, EC135P2+, 

EC135T1, EC135T2, and EC135T2+ 

helicopters. AD 2016–11–21 requires 

revising the life limit of certain parts 

and removing each part that has reached 

its life limit. Since the FAA issued AD 

2016–11–21, new models were certified. 

This proposed AD would expand the 

applicability to include Model EC135P3 

and EC135T3 helicopters. This 

proposed AD would also revise the life 

limits for certain parts and propose to 

remove each part that has reached or 

exceeded its life limit. The actions of 

this proposed AD are intended to 

address an unsafe condition on these 

products. 

DATES: The FAA must receive comments 

on this proposed AD by April 22, 2021. 

ADDRESSES: You may send comments by 

any of the following methods: 

• Federal eRulemaking Docket: Go to 

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

online instructions for sending your 

comments electronically. 

• Fax: 202–493–2251. 

• Mail: Send comments to the U.S. 

Department of Transportation, Docket 

Operations, M–30, West Building 

Ground Floor, Room W12–140, 1200 

New Jersey Avenue SE, Washington, DC 

20590–0001. 

• Hand Delivery: Deliver to the 

‘‘Mail’’ address between 9 a.m. and 5 

p.m., Monday through Friday, except 

Federal holidays. 

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–2019– 

0113; 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 proposed 

AD, the European Aviation Safety 

Agency (now European Union Aviation 

Safety Agency) (EASA) AD, any 

comments received and other 

information. The street address for 

Docket Operations is listed above. 

Comments will be available in the AD 

docket shortly after receipt. 

For service information identified in 

this proposed rule, contact Airbus 

Helicopters, 2701 N. Forum Drive, 

Grand Prairie, TX 75052; telephone 

972–641–0000 or 800–232–0323; fax 

972–641–3775; or at https://

www.airbus.com/helicopters/services/ 

technical-support.html. You may view 

this referenced service information at 

the FAA, Office of the Regional Counsel, 

Southwest Region, 10101 Hillwood 

Pkwy., Room 6N–321, Fort Worth, TX 

76177. 

FOR FURTHER INFORMATION CONTACT: Matt 

Fuller, AD Program Manager, 

Operational Safety Branch, 

Airworthiness Products Section, 

General Aviation & Rotorcraft Unit, 

FAA, 10101 Hillwood Pkwy., Fort 

Worth, TX 76177; telephone 817–222– 

5110; email matthew.fuller@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–2019–0113; Product Identifier 

2017–SW–140–AD’’ 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 this 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.regualtions.gov, including any 

personal information you provide. The 

agency will also post a report 

summarizing each substantive verbal 

contact received about this proposal. 

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 Matt Fuller, AD 

Program Manager, Operational Safety 

Branch, Airworthiness Products 

Section, General Aviation & Rotorcraft 

Unit, 10101 Hillwood Pkwy., Fort 

Worth, TX 76177; telephone 817–222– 

5110; email Matthew.Fuller@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. 

Discussion 

The FAA issued AD 2016–11–21, 

Amendment 39–18548 (81 FR 36137, 

June 6, 2016) (AD 2016–11–21) for 

Airbus Helicopters Model EC135P1, 

EC135P2, EC135P2+, EC135T1, 


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13238 Federal Register / Vol. 86, No. 43 / Monday, March 8, 2021 / Proposed Rules 

EC135T2, and EC135T2+ helicopters. 

AD 2016–11–21 requires reducing the 

life limit of certain parts and removing 

each part that has reached its life limit. 

AD 2016–11–21 was prompted by 

Airbus Helicopters revising the 

airworthiness limitations for the Model 

EC135 and EC635 helicopters’ type 

design as published in the Master 

Servicing Manual (MSM) EC135 Chapter 

04—ALS documents. Revision 14 of the 

MSM contains these new airworthiness 

limitations. 

EASA, which is the Technical Agent 

for the Member States of the European 

Union, issued EASA AD No. 2013–0178, 

dated August 7, 2013 (EASA AD 2013– 

0178), to correct an unsafe condition for 

Eurocopter Deutschland GmbH (ECD) 

(now Airbus Helicopters) Model 

EC135P1, EC135P2, EC135P2+, 

EC135T1, EC135T2, EC135T2+, 

EC635T1, EC635P2+, and EC635T2+ 

helicopters. EASA advises that ECD has 

revised the airworthiness limitations for 

the EC135 and EC635 type design as 

published in the MSM. Revision 14 of 

the MSM contains these new 

airworthiness limitations. EASA states 

that failure to comply with these 

limitations could result in failure of a 

critical part, which could result in loss 

of control of the helicopter. 

Accordingly, EASA AD 2013–0178 

requires revising the airworthiness 

limitations section (ALS) to include the 

new life limits and replacing each part 

that has reached its life limit. 

Actions Since AD 2016–11–21 Was 

Issued 

Since the FAA issued AD 2016–11– 

21, EASA issued EASA AD No. 2017– 

0243, dated December 6, 2017 (EASA 

AD 2017–0243), which supersedes 

EASA AD No. 2013–0178 and expands 

the applicability to include Models 

EC135P3, EC135T3, EC635P3, and 

EC635T3 helicopters. New life limits 

also were added for some parts. Model 

EC635P3 and EC635T3 helicopters are 

not included in the applicability of this 

proposed AD as these model helicopters 

are not FAA type-certificated. 

FAA’s Determination 

These helicopters have been approved 

by EASA and are approved for operation 

in the United States. Pursuant to the 

FAA’s bilateral agreement with the 

European Union, EASA has notified the 

FAA of the unsafe condition described 

in its AD. The FAA is proposing this AD 

after evaluating all known relevant 

information and determining that an 

unsafe condition is likely to exist or 

develop on other helicopters of the same 

type design. 

Related Service Information Under 1 

CFR Part 51 

The FAA reviewed Airbus Helicopters 

Alert Service Bulletin (ASB) EC135– 

04A–012, Revision 0, dated September 

11, 2017, which specifies incorporating 

life limits for the tail rotor hub body 

into the tail rotor hub log card and into 

the list of life-limited parts. Airbus 

Helicopters reports the addition of the 

tail rotor hub body into the tail rotor 

hub log card was prompted by a new, 

recently manufactured, serial-numbered 

hub. 

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 the ADDRESSES section. 

Proposed AD Requirements 

This proposed AD would require, 

before further flight, establishing a life 

limit for the tail rotor hub body of 

27,400 hours time-in-service (TIS) or 

using the service information if the 

history of the tail rotor hub body is not 

known or cannot be identified. This 

proposed AD would also require 

establishing life limits for certain 

swashplate and mixing lever gear unit 

parts in the ALS, and recording the 

revised life limit on the component 

history card or equivalent record. 

Additionally, this proposed AD would 

require continuing to record the life 

limit of certain parts that have not 

reached their life limit. This proposed 

AD would require removing from 

service any part that reached or 

exceeded its life limit. 

Differences Between This Proposed AD 

and the EASA AD 

The EASA AD applies to Model 

EC635P2+, EC635P3, EC635T2+, and 

EC635T3 helicopters, whereas this 

proposed AD would not because these 

model helicopters are not FAA typecertificated. The EASA AD would 

require revising the Aircraft 

Maintenance Program with new or 

revised life limitations within 12 

months after the EASA AD’s effective 

date. This proposed AD would require 

revising the life limit for certain parts in 

the ALS of the existing maintenance 

manual for your helicopter before 

further flight. 

Costs of Compliance 

The FAA estimates that this proposed 

AD would affect 272 helicopters of U.S. 

Registry. The FAA estimates that 

operators may incur the following costs 

in order to comply with this proposed 

AD. Labor costs are estimated at $85 per 

work-hour. 

Revising the component history card 

or equivalent record would take about 2 

work-hours, for an estimated cost of 

$170 per helicopter and $46,240 for the 

U.S. fleet. 

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, I certify 

this proposed regulation: 

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 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: 


jbell on DSKJLSW7X2PROD with PROPOSALS
Federal Register / Vol. 86, No. 43 / Monday, March 8, 2021 / Proposed Rules 13239 

Authority: 49 U.S.C. 106(g), 40113, 44701. 

§ 39.13 [Amended] 

■ 2. The FAA amends § 39.13 by: 

■ a. Removing Airworthiness Directive 

(AD) 2016–11–21, Amendment 39– 

18548 (81 FR 36137); and 

■ b. Adding the following new AD: 

Airbus Helicopters Deutschland GmbH: 

Docket No. FAA–2019–0113; Product 

Identifier 2017–SW–140–AD. 

(a) Applicability 

This airworthiness directive (AD) applies 

to Airbus Helicopters Deutschland GmbH 

Model EC135P1, EC135P2, EC135P2+, 

EC135P3, EC135T1, EC135T2, EC135T2+, 

and EC135T3 helicopters, certificated in any 

category. 

(b) Unsafe Condition 

The FAA is issuing this AD to prevent 

certain parts from remaining in service 

beyond their fatigue life, resulting in failure 

of the part and subsequent loss of control of 

the helicopter. 

(c) Affected ADs 

This AD replaces AD 2016–11–21, 

Amendment 39–18548 (81 FR 36137, June 6, 

2016). 

(d) Comments Due Date 

The FAA must receive comments by April 

22, 2021. 

(e) Compliance 

You are responsible for performing each 

action required by this AD within the 

specified compliance time unless it has 

already been accomplished prior to that time. 

(f) Required Actions 

(1) Before further flight, establish a life 

limit for the tail rotor hub body (hub body), 

part number (P/N) L642A2003102, of 27,400 

hours time-in-service (TIS). If you cannot 

determine the hub body’s TIS, follow the 

instructions in Table 1, Examples and 

Calculations, Effectivity: The history of the 

hub body is not known or can’t be identified, 

in Airbus Helicopters Alert Service Bulletin 

(ASB) EC135–04A–012, Revision 0, dated 

September 11, 2017, except where the service 

information specifies that you contact the 

manufacturer, you are required to remove the 

part from service instead. 

(2) Before further flight, revise the life limit 

for each part listed in paragraphs (f)(2)(i) and 

(ii) of this AD in the Airworthiness 

Limitations Section (ALS) of the existing 

maintenance manual for your helicopter and 

record the revised life limit on the 

component history card or equivalent record 

as follows: 

(i) For swashplate parts: 

(A) The life limit for the ring (control ring), 

P/N L623M2001213, is 10,700 hours TIS. 

(B) The life limit for the cardan ring (twopart), P/N L623M2005205, is 14,300 hours 

TIS. 

(C) The life limit for the bolt (control ring), 

P/N L671M7001215, is 14,300 hours TIS. 

(D) The life limit for the bolt (sliding 

sleeve), P/N L623M2006206 and P/N 

L623M2006213, is 14,300 hours TIS. 

(ii) For mixing lever gear unit parts: 

(A) The life limit for the forked lever 

assembly, P/N L671M3012102, is 10,400 

hours TIS. 

(B) The life limit for the hinged support, 

P/N L671M7003210, is 8,400 hours TIS. 

(C) The life limit for the bolt, P/N 

L671M7001220, is 8,400 hours TIS. 

(3) Before further flight, remove from 

service any part listed in paragraphs (f)(1) 

and (2) of this AD that has reached or 

exceeded its revised life limit. 

(4) Thereafter, for any part listed in 

paragraphs (f)(1) and (2) of this AD that has 

not reached or exceeded its life limit, 

continue to record the life limit of the part 

on its component history card or equivalent 

record and remove any part listed in 

paragraph (f)(1) and (2) of this AD from 

service before the part has reached or 

exceeded its revised life limit. 

(g) Special Flight Permits 

Special flight permits are limited to a 

onetime flight to a maintenance facility to 

replace a part that has reached its life limit. 

(h) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Strategic Policy 

Rotorcraft Section, FAA, has the authority to 

approve AMOCs for this AD, if requested 

using the procedures found in 14 CFR 39.19. 

If sending information directly to the 

manager of the Strategic Policy Rotorcraft 

Section, send it to: Manager, Strategic Policy 

Rotorcraft Section, FAA, 10101 Hillwood 

Pkwy., Fort Worth, TX 76177; telephone 

817–222–5110. Information may be emailed 

to: 9-ASW-FTW-AMOC-Requests@faa.gov. 

(2) For operations conducted under a 14 

CFR part 119 operating certificate or under 

14 CFR part 91, subpart K, the FAA suggests 

that you notify your principal inspector, or 

lacking a principal inspector, the manager of 

the local flight standards district office or 

certificate holding district office before 

operating any aircraft complying with this 

AD through an AMOC. 

(i) Additional Information 

The subject of this AD is addressed in 

European Aviation Safety Agency (now 

European Union Aviation Safety Agency) 

(EASA) AD No. 2017–0243, dated December 

6, 2017. You may view the EASA AD on the 

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

AD Docket. 

(j) Subject 

Joint Aircraft Service Component (JASC) 

Code: 6400, Tail Rotor System. 

Issued on February 17, 2021. 

Lance T. Gant, 

Director, Compliance & Airworthiness 

Division, Aircraft Certification Service. 

[FR Doc. 2021–03991 Filed 3–5–21; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2021–0131; Project 

Identifier MCAI–2020–01628–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 adopt a 

new airworthiness directive (AD) for all 

Airbus SAS Model A330–200, –300, 

–800, and –900 series airplanes; and 

Model A340–200, –300, –500, and –600 

series airplanes. This proposed AD was 

prompted by reports that certain oxygen 

supply solenoid valves are a potential 

source of increased flow resistance 

within the flightcrew oxygen system. 

This proposed AD would require a 

special detailed inspection (flow test) of 

certain solenoid valves, and 

replacement if necessary, 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 April 22, 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 material that will be incorporated 

by reference (IBR) in this AD, 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 

IBR material on the EASA website at 

https://ad.easa.europa.eu. You may 

view this IBR material at the FAA, 

Airworthiness Products Section, 

Operational Safety Branch, 2200 South 

216th St., Des Moines, WA. For 


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