Federal Register / Vol. 86, No. 33 / Monday, February 22, 2021 / Rules and Regulations 10449 

(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 (j) of this AD. 

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

approved AMOC, notify your appropriate 

principal inspector, or lacking a principal 

inspector, the manager of the responsible 

Flight Standards Office. 

(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 Saab AB, Support and Services’ 

EASA Design Organization Approval (DOA). 

If approved by the DOA, the approval must 

include the DOA-authorized signature. 

(j) Related Information 

For more information about this AD, 

contact Shahram Daneshmandi, Aerospace 

Engineer, Large Aircraft Section, 

International Validation Branch, FAA, 2200 

South 216th St., Des Moines, WA 98198; 

phone and fax: 206–231–3220; email: 

shahram.daneshmandi@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 2020–0137, dated June 18, 2020. 

(ii) [Reserved] 

(3) For EASA AD 2020–0137, contact the 

EASA, Konrad-Adenauer-Ufer 3, 50668 

Cologne, Germany; phone: +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 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–2020–0855. 

(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 January 4, 2021. 

Lance T. Gant, 

Director, Compliance & Airworthiness 

Division, Aircraft Certification Service. 

[FR Doc. 2021–01824 Filed 2–19–21; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2020–1037; Project 

Identifier 2019–SW–077–AD; Amendment 

39–21407; AD 2021–03–04] 

RIN 2120–AA64 

Airworthiness Directives; Airbus 

Helicopters Deutschland GmbH 

Helicopters 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: The FAA is adopting a new 

airworthiness directive (AD) for certain 

Airbus Helicopters Deutschland GmbH 

Model EC135P1, EC135P2, EC135P2+, 

EC135P3, EC135T1, EC135T2, 

EC135T2+, and EC135T3 helicopters. 

This AD requires removing certain 

Titanium (Ti) bolts from service and 

prohibits installing these Ti-bolts in a 

critical area. This AD was prompted by 

a report of a broken Ti-bolt. The actions 

of this AD are intended to address an 

unsafe condition on these products. 

DATES: This AD is effective March 29, 

2021. 

ADDRESSES: For service information 

identified in this final 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 

the referenced service information at the 

FAA, Office of the Regional Counsel, 

Southwest Region, 10101 Hillwood 

Pkwy., Room 6N–321, Fort Worth, TX 

76177. 

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– 

1037; or in person at Docket Operations 

between 9 a.m. and 5 p.m., Monday 

through Friday, except Federal holidays. 

The AD docket contains this AD, the 

European Union Aviation Safety Agency 

(EASA) AD, any comments received, 

and other information. The street 

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: 

Katherine Venegas, Aviation Safety 

Engineer, Los Angeles ACO, FAA, 3960 

Paramount Blvd., Lakewood, CA 90712; 

telephone 562–627–5353; email 

katherine.venegas@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Discussion 

The FAA issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 by adding an AD that would 

apply to Airbus Helicopters 

Deutschland GmbH Model EC135P1, 

EC135P2, EC135P2+, EC135P3, 

EC135T1, EC135T2, EC135T2+, and 

EC135T3 helicopters with a Ti-bolt part 

number (P/N) L535M2001203 marked 

with manufacturer monogram ‘‘D’’ or 

with an illegible manufacturer 

monogram installed on the forward tail 

rotor (T/R) drive shaft. The NPRM 

published in the Federal Register on 

November 30, 2020 (85 FR 76490). The 

NPRM proposed to require removing 

any affected Ti-bolt installed on the 

forward T/R drive shaft from service 

and prohibit installing an affected Tibolt on the forward T/R drive shaft of 

any helicopter. The proposed 

requirements were intended to prevent 

failure of an affected Ti-bolt installed in 

a critical location, possibly resulting in 

reduced control of the helicopter. 

The NPRM was prompted by EASA 

AD No. 2019–0199, dated August 16, 

2019, issued by EASA, which is the 

Technical Agent for the Member States 

of the European Union, to correct an 

unsafe condition for Airbus Helicopters 

Deutschland GmbH (AHD), formerly 

Eurocopter Deutschland GmbH, 

Eurocopter Espan ̃ a S.A., Model EC135 

P1, EC135 P2, EC135 P2+, EC135 P3, 

EC135 T1, EC135 T2, EC135 T2+, EC135 

T3, EC635 P2+, EC635 P3, EC635 T1, 

EC635 T2+, and EC635 T3 helicopters. 

EASA advises of a report of a broken Tibolt. Subsequent investigation revealed 

that an improper heat treatment process 

was accomplished on a batch of Tibolts, which can lead to hydrogen 

embrittlement. The investigation also 

identified the critical location where 

these Ti-bolts are installed on 

helicopters. According to EASA, this 

condition, if not detected and corrected, 

could lead to failure of an affected Tibolt installed in a critical location, 

possibly resulting in reduced control of 

the helicopter. Accordingly, the EASA 

AD requires a one-time inspection of Tibolt P/N L535M2001203 marked with 


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10450 Federal Register / Vol. 86, No. 33 / Monday, February 22, 2021 / Rules and Regulations 

manufacturer monogram ‘‘D’’ or with an 

illegible manufacturer monogram 

installed on the forward T/R drive shaft 

and, depending on the inspection 

results, replacing the Ti-bolt. The EASA 

AD also prohibits the (re)installation of 

these Ti-bolts. 

Comments 

The FAA gave the public the 

opportunity to participate in developing 

this final rule, but the FAA did not 

receive any comments on the NPRM or 

on the determination of the cost to the 

public. 

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 issuing this AD 

after evaluating all of the information 

provided by EASA and determining the 

unsafe condition exists and is likely to 

exist or develop on other helicopters of 

these same type designs and that air 

safety and the public interest require 

adopting the AD requirements as 

proposed. 

Differences Between This AD and the 

EASA AD 

The EASA AD applies to Model 

EC135 P1, EC135 P2, EC135 P2+, EC135 

P3, EC135 T1, EC135 T2, EC135 T2+, 

EC135 T3, EC635 P2+, EC635 P3, EC635 

T1, EC635 T2+, and EC635 T3 

helicopters and requires inspecting Tibolt P/N L535M2001203 marked with 

manufacturer monogram ‘‘D’’ or with an 

illegible manufacturer monogram 

installed on the forward T/R drive shaft. 

This AD applies to Model EC135P1, 

EC135P2, EC135P2+, EC135P3, 

EC135T1, EC135T2, EC135T2+, and 

EC135T3 helicopters with a Ti-bolt P/N 

L535M2001203 marked with 

manufacturer monogram ‘‘D’’ or with an 

illegible manufacturer monogram 

installed on the forward T/R drive shaft 

instead. This AD does not apply to 

Model EC635 P2+, EC635 P3, EC635 T1, 

EC635 T2+, or EC635 T3 helicopters 

because these models are not FAA typecertificated. The EASA AD requires 

discarding the affected Ti-bolts, whereas 

this AD requires removing the affected 

Ti-bolts from service instead. 

Related Service Information 

The FAA reviewed Airbus Helicopters 

Alert Service Bulletin (ASB) No. EC135– 

00A–001, Revision 1, dated September 

2, 2019, for Airbus Helicopters 

Deutschland GmbH Model EC135 T1, 

T2, T2+, T3, P1, P2, P2+, P3, 635 T1, 

635 T2+, 635 T3, 635 P2+, and 635 P3 

helicopters, and Airbus Helicopters ASB 

No. EC135H–00A–001, Revision 1, 

dated September 2, 2019, for Airbus 

Helicopters Deutschland GmbH Model 

EC135, T3H, P3H, 635 T3H, and 635 

P3H helicopters. This service 

information specifies inspecting the 

forward T/R drive shaft, distance plate 

of the 5B–0.50–2.50P–XN–1 antenna, 

main rotor controls, FWD connection of 

ball bearing control, and AFT 

connection of ball bearing control and 

yaw actuator for the installation of Tibolt P/N L535M2001203, EN3308– 

040020F, L221M1040201, EN3740– 

060020F, and EN3308–060020F, marked 

with manufacturer monogram ‘‘D’’ or an 

illegible manufacturer monogram. If a 

specified Ti-bolt is installed, the service 

information specifies replacing the Tibolt and discarding the removed Ti-bolt. 

Costs of Compliance 

The FAA estimates that this AD 

affects 326 helicopters of U.S. Registry. 

Labor rates are estimated at $85 per 

work-hour. Based on these numbers, the 

FAA estimates that operators may incur 

the following costs in order to comply 

with this AD. 

Replacing a Ti-bolt takes about four 

work-hours and parts cost about $82 for 

an estimated cost of $422 per Ti-bolt. 

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 helicopters 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. 

Adoption of 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: 

2021–03–04 Airbus Helicopters 

Deutschland GmbH: Amendment 39– 

21407; Docket No. FAA–2020–1037; 

Project Identifier 2019–SW–077–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, with a Titanium (Ti) bolt part 

number L535M2001203 marked with 

manufacturer monogram ‘‘D’’ or with an 

illegible manufacturer monogram installed 

on the forward tail rotor drive shaft. 

Note 1 to paragraph (a): Helicopters with 

an EC135P3H designation are Model 

EC135P3 helicopters. Helicopters with an 

EC135T3H designation are Model EC135T3 

helicopters. 

(b) Unsafe Condition 

This AD defines the unsafe condition as 

failure of an affected Ti-bolt installed in a 

critical location, possibly resulting in 

reduced control of the helicopter. 

(c) Effective Date 

This AD becomes effective March 29, 2021. 

(d) 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. 


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Federal Register / Vol. 86, No. 33 / Monday, February 22, 2021 / Rules and Regulations 10451 

(e) Required Actions 

(1) Within 50 hours time-in-service or 3 

months, whichever occurs first, remove any 

Ti-bolt identified in paragraph (a) of this AD, 

located on the forward tail rotor drive shaft, 

from service. 

(2) As of the effective date of this AD, do 

not install a Ti-bolt identified in paragraph 

(a) of this AD on the forward tail rotor drive 

shaft of any helicopter. 

(f) 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) 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. 

(g) Additional Information 

(1) Airbus Helicopters Alert Service 

Bulletin (ASB) No. EC135–00A–001 and ASB 

No. EC135H–00A–001, each Revision 1 and 

dated September 2, 2019, which are not 

incorporated by reference, contain additional 

information about the subject of this AD. For 

service information identified in this AD, 

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 a copy of the service 

information at the FAA, Office of the 

Regional Counsel, Southwest Region, 10101 

Hillwood Pkwy, Room 6N–321, Fort Worth, 

TX 76177. 

(2) The subject of this AD is addressed in 

European Union Aviation Safety Agency 

(EASA) AD No. 2019–0199, dated August 16, 

2019. You may view the EASA AD on the 

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

Docket No. FAA–2020–1037. 

(h) Subject 

Joint Aircraft Service Component (JASC) 

Code: 1430, Fasteners; and 6510, Tail Rotor 

Drive Shaft. 

Issued on January 22, 2021. 

Lance T. Gant, 

Director, Compliance & Airworthiness 

Division, Aircraft Certification Service. 

[FR Doc. 2021–01848 Filed 2–19–21; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2020–0849; Project 

Identifier MCAI–2020–01036–A; Amendment 

39–21374; AD 2020–26–19] 

RIN 2120–AA64 

Airworthiness Directives; Pilatus 

Aircraft Ltd. Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: The FAA is adopting a new 

airworthiness directive (AD) for all 

Pilatus Aircraft Ltd. Model PC–7 

airplanes. This AD results from 

mandatory continuing airworthiness 

information (MCAI) originated by an 

aviation authority of another country to 

identify and correct an unsafe condition 

on an aviation product. This AD 

requires revising the Airworthiness 

Limitations section (ALS) of the existing 

aircraft maintenance manual (AMM) to 

introduce new mandatory repetitive 

inspections for the flap pivot arm 

assemblies and for certain wing angle 

brackets, and to implement a change to 

the Oxygen cylinder and pressure 

reducer task item. The FAA is issuing 

this AD to address the unsafe condition 

on these products. 

DATES: This AD is effective March 29, 

2021. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of March 29, 2021. 

ADDRESSES: For service information 

identified in this final rule, contact 

Pilatus Aircraft Ltd., CH–6371, 

Customer Technical Support (MCC), 

P.O. Box 992, CH–6371, Stans, 

Switzerland; phone: +41 (0)41 619 67 

74; fax: +41 (0)41 619 67; email: 

techsupport@pilatus-aircraft.com; 

website: https://www.pilatusaircraft.comen/. You may view this 

service information at the FAA, 

Airworthiness Products Section, 

Operational Safety Branch, 901 Locust, 

Kansas City, Missouri 64106. For 

information on the availability of this 

material at the FAA, call (816) 329– 

4148. It is also available at https://

www.regulations.gov by searching for 

and locating Docket No. FAA–2020– 

0849. 

Examining the AD Docket 

You may examine the AD docket at 

https://www.regulations.gov by 

searching for and locating Docket No. 

FAA–2020–0849; 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, the MCAI, any comments 

received, and other information. The 

address for Docket Operations is U.S. 

Department of Transportation, Docket 

Operations, M–30, West Building 

Ground Floor, Room W12–140, 1200 

New Jersey Avenue SE, Washington, DC 

20590. 

FOR FURTHER INFORMATION CONTACT: 

Doug Rudolph, Aerospace Engineer, 

FAA, General Aviation & Rotorcraft 

Section, International Validation 

Branch, 901 Locust, Room 301, Kansas 

City, Missouri 64106; phone: (816) 329– 

4059; fax: (816) 329–4090; email: 

doug.rudolph@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 Pilatus Aircraft Ltd. Model 

PC–7 airplanes. The NPRM published in 

the Federal Register on September 24, 

2020 (85 FR 60097). The NPRM was 

prompted by MCAI originated by the 

Federal Office for Civil Aviation 

(FOCA), which is the aviation authority 

for Switzerland. FOCA has issued FOCA 

AD HB–2020–007, dated July 23, 2020 

(referred to after this as the MCAI), to 

correct an unsafe condition with new 

mandatory instructions for continued 

airworthiness for all Pilatus Aircraft Ltd. 

Model PC–7 airplanes. The MCAI states: 

The airworthiness limitations and 

certification maintenance instructions for 

Pilatus PC–7 aeroplanes, which are approved 

by FOCA, are currently defined and 

published in the Pilatus PC–7 AMM Chapter 

5. These instructions have been identified as 

mandatory for continued airworthiness. 

Failure to accomplish these instructions 

could result in an unsafe condition 

[discrepancies of life-limited and overhauled 

components, which could result in reduced 

structural integrity and system reliability of 

the airplane]. 

Previously, FOCA issued AD HB–2019–004 

(later corrected) to require implementation of 

the maintenance tasks and airworthiness 

limitations as specified in Pilatus PC–7 AMM 

Document Number 01715, or Document 

Number 02416, both at issue 44, as 

applicable. [These tasks included the added 

wing angle bracket at rib 23 repetitive 

inspections.] 

Since that AD was issued, Pilatus amended 

the ALS, as defined in this AD, to introduce 

new mandatory repetitive inspection for the 

flap pivot arm assemblies and a change to the 

Oxygen cylinder and pressure reducer task 

(Chapter 35—Oxygen) to remove the 

reference to the part numbers. 

For the reason described above, this 

[Swiss] AD retains the requirements of FOCA 


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