Federal Register / Vol. 86, No. 103 / Tuesday, June 1, 2021 / Rules and Regulations 29183 

(a) Effective Date 

This airworthiness directive (AD) becomes 

effective June 16, 2021. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to Airbus SAS Model 

A319–111, –112, –113, –114, –115, –131, 

–132, and –133 airplanes, certificated in any 

category, as identified in European Union 

Aviation Safety Agency (EASA) AD 2020– 

0218, dated October 12, 2020 (EASA AD 

2020–0218). 

(d) Subject 

Air Transport Association (ATA) of 

America Code 53, Fuselage. 

(e) Reason 

This AD was prompted by a determination 

that the cabin swift broadband antenna 

doubler installation does not meet 

widespread fatigue damage (WFD) 

requirements. The FAA is issuing this AD to 

address the potential effects of WFD on the 

installation. This condition, if not corrected, 

could reduce the structural integrity of the 

fuselage. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Requirements 

Except as specified in paragraph (h) of this 

AD: Comply with all required actions and 

compliance times specified in, and in 

accordance with, EASA AD 2020–0218. 

(h) Exceptions to EASA AD 2020–0218 

(1) Where EASA AD 2020–0218 refers to its 

effective date, this AD requires using the 

effective date of this AD. 

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

2020–0218 does not apply to this AD. 

(3) Where paragraph (3) of EASA AD 2020– 

0218 specifies actions if ‘‘any discrepancy is 

detected,’’ for this AD a ‘‘discrepancy’’ is 

defined as any crack, oversized hole, 

corrosion, or other damage. 

(4) Where paragraph (3) of EASA AD 2020– 

0218 specifies to ‘‘contact Airbus for 

applicable corrective actions,’’ if corrective 

actions are associated with cracking, the 

cracking must be repaired before further 

flight 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. 

(i) 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 (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 Airbus SAS’s EASA DOA. If 

approved by the DOA, the approval must 

include the DOA-authorized signature. 

(3) Required for Compliance (RC): Except 

as required by paragraph (i)(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. 

(j) Related Information 

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. 

(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 2020–0218, dated October 12, 

2020. 

(ii) [Reserved] 

(3) For EASA AD 2020–0218, 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. 

(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–2021–0367. 

(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 May 7, 2021. 

Lance T. Gant, 

Director, Compliance & Airworthiness 

Division, Aircraft Certification Service. 

[FR Doc. 2021–11428 Filed 5–28–21; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2021–0126; Project 

Identifier MCAI–2020–00266–R; Amendment 

39–21556; AD 2021–10–23] 

RIN 2120–AA64 

Airworthiness Directives; Airbus 

Helicopters Deutschland GmbH (AHD) 

Helicopters 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: The FAA is adopting a new 

airworthiness directive (AD) for Airbus 

Helicopters Deutschland GmbH (AHD) 

Model MBB–BK 117 D–2 helicopters. 

This AD was prompted by a report of a 

broken Titanium (Ti) bolt. This AD 

requires removing certain Ti-bolts from 

service and prohibits installing these Tibolts in a critical area. The FAA is 

issuing this AD to address the unsafe 

condition on these products. 

DATES: This AD is effective July 6, 2021. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain document listed in this AD 

as of July 6, 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. It is also available at https://

www.regulations.gov by searching for 

and locating Docket No. FAA–2021– 

0126. 

Examining the AD Docket 

You may examine the AD docket at 

https://www.regulations.gov by 


jbell on DSKJLSW7X2PROD with RULES
29184 Federal Register / Vol. 86, No. 103 / Tuesday, June 1, 2021 / Rules and Regulations 

searching for and locating Docket No. 

FAA–2021–0126; 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 European Union Aviation 

Safety Agency (EASA) AD, any service 

information that is incorporated by 

reference, 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: Matt 

Fuller, AD Program Manager, General 

Aviation & Rotorcraft Unit, 

Airworthiness Products Section, 

Operational Safety Branch, FAA, 10101 

Hillwood Pkwy., Fort Worth, TX 76177; 

telephone (817) 222–5110; email 

matthew.fuller@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 Airbus Helicopters 

Deutschland GmbH (AHD) Model MBB– 

BK 117 D–2 helicopters with a Ti-bolt 

part number (P/N) EN3740–060022F 

marked with manufacturer monogram 

‘‘D’’ or with an illegible manufacturer 

monogram, installed on the aft 

connection of the tail rotor ball bearing 

control. The NPRM published in the 

Federal Register on March 3, 2021 (86 

FR 12294). In the NPRM, the FAA 

proposed to require removing any 

affected Ti-bolt P/N EN3740–060022F 

from service. The NPRM also to prohibit 

installing an affected Ti-bolt on the aft 

connection of the ball bearing control of 

any helicopter. The NPRM was 

prompted by EASA AD 2019–0258, 

dated October 18, 2019 (EASA AD 

2019–0258), 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, Model MBB–BK117 D–2 

helicopters. EASA advises of a report of 

a broken Ti-bolt. Subsequent 

investigation revealed that an improper 

heat treatment process was 

accomplished on a batch of Ti-bolts, 

which can lead to hydrogen 

embrittlement. Hydrogen embrittlement 

can make high-strength bolts susceptible 

to stress corrosion, pitting, and failure. 

EASA states that this condition, if not 

detected and corrected, could lead to 

failure of an affected Ti-bolt installed in 

a critical location, possibly resulting in 

reduced control of the helicopter. 

Accordingly, EASA AD 2019–0258 

requires a one-time inspection for Tibolt P/N EN3740–060022F marked with 

manufacturer monogram ‘‘D’’ or with an 

illegible manufacturer monogram 

installed on the aft connection of the tail 

rotor ball bearing control (ball bearing 

control) and, depending on findings, 

contacting AHD for corrective action. 

EASA AD 2019–0258 also prohibits the 

(re)installation of these Ti-bolts. 

Discussion of Final Airworthiness 

Directive 

Comments 

The FAA received no comments on 

the NPRM or on the determination of 

the costs. 

Conclusion 

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 about the unsafe condition 

described in its AD. The FAA reviewed 

the relevant data 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 helicopters. 

Related Service Information Under 1 

CFR Part 51 

The FAA reviewed Airbus Helicopters 

Alert Service Bulletin No. ASB MBB– 

BK117 D–2–00A–001, Revision 1, dated 

October 16, 2019, which specifies 

replacing each Ti-bolt P/N EN3740– 

060022F that is marked with 

manufacturer monogram ‘‘D’’ or if the 

manufacturer monogram cannot be 

identified with an airworthy Ti-bolt in 

both locations of the aft connection of 

ball bearing control and both high 

frequency (HF) antenna bracket 

locations. 

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. 

Differences Between This AD and the 

EASA AD 

EASA AD 2019–0258 applies to 

Model MBB–BK117 D–2 helicopters and 

requires inspecting for Ti-bolt P/N 

EN3740–060022F marked with 

manufacturer monogram ‘‘D’’ or with an 

illegible manufacturer monogram 

installed on the aft connection of the 

ball bearing control. This AD applies to 

Model MBB–BK 117 D–2 helicopters 

with a Ti-bolt P/N EN3740–060022F 

marked with manufacturer monogram 

‘‘D’’ or with an illegible manufacturer 

monogram installed on the aft 

connection of the ball bearing control 

instead. EASA AD 2019–0258 requires 

contacting AHD for approved 

instructions if an affected Ti-bolt is 

found, whereas this AD requires 

removing an affected Ti-bolt from 

service instead. 

Costs of Compliance 

The FAA estimates that this AD 

affects 29 helicopters of U.S. Registry. 

Labor rates are estimated at $85 per 

work-hour. Based on these numbers, the 

FAA estimates the following costs to 

comply with this AD. 

Replacing a Ti-bolt takes about 2 

work-hours and parts cost about $100 

for an estimated cost of $270 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. 


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Federal Register / Vol. 86, No. 103 / Tuesday, June 1, 2021 / Rules and Regulations 29185 

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: 

2021–10–23 Airbus Helicopters 

Deutschland GmbH (AHD): Amendment 

39–21556; Docket No. FAA–2021–0126; 

Project Identifier MCAI–2020–00266–R. 

(a) Effective Date 

This airworthiness directive (AD) is 

effective July 6, 2021. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to Airbus Helicopters 

Deutschland GmbH (AHD) Model MBB–BK 

117 D–2 helicopters, certificated in any 

category, with a Titanium (Ti) bolt part 

number EN3740–060022F marked with 

manufacturer monogram ‘‘D’’ or with an 

illegible manufacturer monogram, installed 

on the aft connection of the tail rotor ball 

bearing control. 

(d) Subject 

Joint Aircraft Service Component (JASC) 

Codes: 1430, Fasteners; and 6720, Tail Rotor 

Control System. 

(e) Unsafe Condition 

This AD was prompted by a Ti-bolt with 

hydrogen embrittlement. This condition 

could result in failure of the tail rotor ball 

bearing control Ti-bolt and subsequent loss of 

tail rotor control. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Required Actions 

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

months, whichever occurs first, remove any 

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

located on the aft connection of the tail rotor 

ball bearing rod end (item 5) and at the input 

lever (item 2) as shown in Figure 1 to Airbus 

Helicopters Alert Service Bulletin No. ASB 

MBB–BK117 D–2–00A–001, Revision 1, 

dated October 16, 2019, from service. 

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

not install a Ti-bolt identified in paragraph 

(c) of this AD on the aft connection of the tail 

rotor ball bearing control of any helicopter. 

(h) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, 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 local 

Flight Standards District Office, as 

appropriate. If sending information directly 

to the manager of the International Validation 

Branch, send it to the attention of the person 

identified in paragraph (i)(1) of this AD. 

Information may be emailed to: 9-AVS-AIR730-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. 

(i) Related Information 

(1) For more information about this AD, 

contact Matt Fuller, AD Program Manager, 

General Aviation & Rotorcraft Unit, 

Airworthiness Products Section, Operational 

Safety Branch, FAA, 10101 Hillwood Pkwy., 

Fort Worth, TX 76177; telephone (817) 222– 

5110; email matthew.fuller@faa.gov. 

(2) The subject of this AD is addressed in 

European Union Aviation Safety Agency 

(EASA) AD 2019–0258, dated October 18, 

2019. You may view the EASA AD at https:// 

www.regulations.gov in Docket No. FAA– 

2021–0126. 

(j) Material Incorporated by Reference 

(1) The Director of the Federal Register 

approved the incorporation by reference 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) Airbus Helicopters Alert Service 

Bulletin No. ASB MBB–BK117 D–2–00A– 

001, Revision 1, dated October 16, 2019. 

(ii) [Reserved] 

(3) 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. 

(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. 

(5) You may view this service information 

that is incorporated by reference at the 

National Archives and Records 

Administration (NARA). For information on 

the availability of this material at NARA, 

email: fedreg.legal@nara.gov, or go to: 

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

ibr-locations.html. 

Issued on May 7, 2021. 

Gaetano A. Sciortino, 

Deputy Director for Strategic Initiatives, 

Compliance & Airworthiness Division, 

Aircraft Certification Service. 

[FR Doc. 2021–11392 Filed 5–28–21; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2021–0097; Project 

Identifier MCAI–2020–01334–T; Amendment 

39–21559; AD 2021–10–26] 

RIN 2120–AA64 

Airworthiness Directives; Bombardier, 

Inc., 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 

Bombardier, Inc., Model BD–100–1A10 

airplanes. This AD was prompted by 

reports of DC motor pump (DCMP) 

failures during production flight tests. 

This AD requires installing a redesigned 

DCMP electric motor assembly. The 

FAA is issuing this AD to address the 

unsafe condition on these products. 

DATES: This AD is effective July 6, 2021. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of July 6, 2021. 

ADDRESSES: For service information 

identified in this final rule, contact 

Bombardier, Inc., 200 Coˆte-Vertu Road 

West, Dorval, Que ́bec H4S 2A3, Canada; 

North America toll-free telephone 

1–866–538–1247 or direct-dial 

telephone 1–514–855–2999; email 

ac.yul@aero.bombardier.com; internet 

https://www.bombardier.com. You may 

view this service information 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 on the internet at 

https://www.regulations.gov by 

searching for and locating Docket No. 

FAA–2021–0097. 

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–2021– 

0097; or in person at Docket Operations 


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