Federal Register / Vol. 87, No. 107 / Friday, June 3, 2022 / Rules and Regulations 33627 

(h) Exceptions to ANAC Emergency AD 

2022–05–02 

(1) Where ANAC Emergency AD 2022–05– 

02 refers to its effective date, this AD requires 

using the effective date of this AD. 

(2) For the first column heading of table 

1—‘‘Compliance Times’’ of ANAC 

Emergency AD 2022–05–02, replace ‘‘Flight 

Hours (FH) accumulated from installation of 

affected PN’’ with ‘‘Flight Hours (FH) 

accumulated from installation of affected PN 

as of the effective date of this (FAA) AD.’’ 

(3) Where table 1—‘‘Compliance Times’’ of 

ANAC Emergency AD 2022–05–02 specifies 

flight hours of ‘‘19.800 or greater,’’ for this 

AD use flight hours of ‘‘19.800 or greater.’’ 

(4) Where paragraphs (a)(i) and (a)(ii) of 

ANAC Emergency AD 2022–05–02 specify 

correcting ‘‘discrepancies,’’ this AD defines a 

discrepancy as a crack. 

(5) The inspections and corrective actions 

specified in paragraphs (a)(i) and (a)(ii) of 

ANAC Emergency AD 2022–05–02 must be 

done using the service information specified 

in paragraphs (a)(i) and (a)(ii) of ANAC 

Emergency AD 2022–05–02. 

(6) Where paragraph (a)(iii) of ANAC 

Emergency AD 2022–05–02 specifies to 

‘‘Modify task 57–30–002–0002 of the 

Airworthiness Limitations Section, on MRB 

1621, APPENDIX A—PART 2— 

AIRWORTHINESS LIMITATION 

INSPECTIONS (ALI)—STRUCTURES, to 

revise its compliance interval’’ at the times 

in table 1—‘‘Compliance Times’’ of ANAC 

Emergency AD 2022–05–02, this AD requires 

revising the existing maintenance or 

inspection program, as applicable, within 30 

days after the effective date of this AD to 

incorporate the information specified in table 

2—‘‘Airworthiness Limitations Section 

Updates’’ of ANAC Emergency AD 2022–05– 

02; except do not include the information in 

the ‘‘Current Threshold/Interval’’ column. 

The initial compliance time for the 

airworthiness limitations task is within 1,000 

flight hours after accomplishment of the tasks 

specified in paragraphs (a)(i) and (a)(ii) of 

ANAC Emergency AD 2022–05–02; except, 

for airplanes that have accumulated 7,499 

flight hours or less from installation of an 

affected part number, as defined in ANAC 

Emergency AD 2022–05–02, the initial 

compliance time is before the accumulation 

of 10,000 flight hours from installation of the 

affected part number. 

(7) Paragraph (b) of ANAC Emergency AD 

2022–05–02 specifies to report crack findings 

to Embraer and ANAC within a certain 

compliance time. For this AD, report crack 

findings at the applicable time specified in 

paragraph (h)(7)(i) or (ii) of this AD. 

(i) If the inspection was done on or after 

the effective date of this AD: Submit the 

report within 36 hours after accomplishment 

of the inspection. 

(ii) If the inspection was done before the 

effective date of this AD: Submit the report 

within 36 hours after the effective date of this 

AD. 

(8) The ‘‘Alternative method of compliance 

(AMOC)’’ section of ANAC Emergency AD 

2022–05–02 does not apply to this AD. 

(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 

ANAC; or ANAC’s authorized Designee. If 

approved by the ANAC Designee, the 

approval must include the Designee’s 

authorized signature. 

(j) Related Information 

For more information about this AD, 

contact Krista Greer, Aerospace Engineer, 

Large Aircraft Section, FAA, International 

Validation Branch, 2200 South 216th St., Des 

Moines, WA 98198; telephone 206–231– 

3221; email Krista.Greer@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) Ageˆncia Nacional de Aviac ̧a ̃o Civil 

(ANAC) Emergency AD 2022–05–02, 

effective May 13, 2022. 

(ii) [Reserved] 

(3) For ANAC Emergency AD 2022–05–02, 

contact ANAC, Aeronautical Products 

Certification Branch (GGCP), Rua Dr. Orlando 

Feirabend Filho, 230—Centro Empresarial 

Aquarius—Torre B—Andares 14 a 18, Parque 

Residencial Aquarius, CEP 12.246–190—Sa ̃o 

Jose ́ dos Campos—SP, Brazil; telephone 55 

(12) 3203–6600; email: pac@anac.gov.br; 

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

this IBR material on the ANAC website at 

https://sistemas.anac.gov.br/certificacao/DA/ 

DAE.asp. 

(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. 

(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 fr.inspection@nara.gov, or go to: 

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

ibr-locations.html. 

Issued on May 26, 2022. 

Gaetano A. Sciortino, 

Deputy Director for Strategic Initiatives, 

Compliance & Airworthiness Division, 

Aircraft Certification Service. 

[FR Doc. 2022–11962 Filed 6–2–22; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2022–0143; Project 

Identifier MCAI–2021–01401–T; Amendment 

39–22061; AD 2022–11–11] 

RIN 2120–AA64 

Airworthiness Directives; De Havilland 

Aircraft of Canada Limited (Type 

Certificate Previously Held by 

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 

De Havilland Aircraft of Canada Limited 

(type certificate previously held by 

Bombardier, Inc.) Model DHC–8–401 

and –402 airplanes. This AD was 

prompted by reports of a certain bolt at 

the pivot pin link being found missing 

or having stress corrosion cracking. This 

AD requires a modification to the nose 

landing gear (NLG) shock strut 

assembly. The FAA is issuing this AD 

to address the unsafe condition on these 

products. 

DATES: This AD is effective July 8, 2022. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of July 8, 2022. 

ADDRESSES: For service information 

identified in this final rule, contact De 

Havilland Aircraft of Canada Limited, 

Q-Series Technical Help Desk, 123 

Garratt Boulevard, Toronto, Ontario 

M3K 1Y5, Canada; telephone 416–375– 

4000; fax 416–375–4539; email thd@

dehavilland.com; internet https://

dehavilland.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–2022–0143. 


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33628 Federal Register / Vol. 87, No. 107 / Friday, June 3, 2022 / Rules and Regulations 

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–2022– 

0143; or in person at Docket Operations 

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

through Friday, except Federal holidays. 

The AD docket contains this final rule, 

any comments received, and other 

information. The address for Docket 

Operations is U.S. Department of 

Transportation, Docket Operations, M– 

30, West Building Ground Floor, Room 

W12–140, 1200 New Jersey Avenue SE, 

Washington, DC 20590. 

FOR FURTHER INFORMATION CONTACT: 

Antariksh Shetty, Aerospace Engineer, 

Airframe and Propulsion Section, FAA, 

New York ACO Branch, 1600 Stewart 

Avenue, Suite 410, Westbury, NY 

11590; telephone 516–228–7300; email 

9-avs-nyaco-cos@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Background 

Transport Canada Civil Aviation 

(TCCA), which is the aviation authority 

for Canada, has issued AD CF–2009– 

29R4, dated October 1, 2021 (TCCA AD 

CF–2009–29R4) (also referred to after 

this as the Mandatory Continuing 

Airworthiness Information, or the 

MCAI), to correct an unsafe condition 

for certain De Havilland Aircraft of 

Canada Limited Model DHC–8–401 and 

–402 airplanes. You may examine the 

MCAI in the AD docket on the internet 

at https://www.regulations.gov by 

searching for and locating Docket No. 

FAA–2022–0143. 

The FAA issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 by adding an AD that would 

apply to certain De Havilland Aircraft of 

Canada Limited (type certificate 

previously held by Bombardier, Inc.) 

Model DHC–8–401 and –402 airplanes. 

The NPRM published in the Federal 

Register on February 23, 2022 (87 FR 

10112). The NPRM was prompted by 

reports of a certain bolt at the pivot pin 

link being found missing or having 

stress corrosion cracking. The NPRM 

proposed to require a modification to 

the NLG shock strut assembly. The FAA 

is issuing this AD to address failure of 

the pivot pin retention bolt, which 

could result in a loss of directional 

control or loss of an NLG tire during 

takeoff or landing, which could lead to 

runway excursions. See the MCAI for 

additional background information. 

Discussion of Final Airworthiness 

Directive 

Comments 

The FAA received comments from Air 

Line Pilots Association, International 

(ALPA), who supported the NPRM 

without change. 

The FAA received additional 

comments from Horizon Air. The 

following presents the comments 

received on the NPRM and the FAA’s 

response to each comment. 

Request to Issue a Single AD 

Horizon Air requested that the FAA 

issue a single AD instead of both AD 

2021–25–12, Amendment 39–21856 (86 

FR 72174, December 21, 2021) (AD 

2021–25–12), and this AD. Horizon Air 

noted that in the ‘‘Relationship Between 

Proposed AD and AD 2021–25–12’’ 

paragraph of the NPRM, it stated it was 

determined that a stand-alone AD 

would be more appropriate. Horizon Air 

pointed out this AD and AD 2021–25– 

12 were both prompted by the same 

unsafe condition and the applicability is 

the same. Horizon Air suggested that 

this final rule replace AD 2021–25–12 in 

order to have the subject matter 

mandates in a singular rule. Horizon Air 

concluded that having the new AD state 

the retained requirements and new 

requirements would promote 

compliance, be historically consistent, 

and be congruent with the related 

Transport Canada airworthiness 

directive (TCCA AD CF–2009–29R4). 

The FAA disagrees with the 

commenter’s request. The FAA 

acknowledges that a single AD is 

typically more appropriate. However, 

AD 2021–25–12 is an immediately 

adopted rule (i.e., a final rule; request 

for comment) that includes actions with 

short compliance times. The FAA could 

not include Part I of TCCA AD CF– 

2009–29R4 in AD 2021–25–12 due to 

the longer compliance time for the 

required modification, which 

necessitated issuing an NPRM with a 

public comment period. The FAA 

considered superseding AD 2021–25–12 

to include retained actions and the 

modification, which has a 1,600 flight 

cycles or 9-month compliance time. 

However, issuing an NPRM to supersede 

AD 2021–25–12 would have delayed the 

rulemaking process. The FAA 

determined issuing a stand-alone NPRM 

for the modification addresses the 

unsafe condition in a timely manner as 

the final rule for the stand-alone NPRM 

(this AD) will be published sooner than 

when a final rule for an NPRM that 

supersedes AD 2021–25–12 would be 

published. The FAA has not changed 

this AD in this regard. 

Request To Include a Statement To 

Indicate the Association With AD 2021– 

25–12 

Horizon Air requested that the FAA 

include a statement to indicate the 

association with AD 2021–25–12. 

Horizon Air stated that the actions 

required by AD 2021–25–12 are only 

applicable to airplanes with pivot pin 

retention bolt part number (P/N) 

NAS6204–14D installed on the NLG 

assembly; consequently, if this part is 

not installed the rule is not applicable. 

Horizon Air also stated that this AD 

mandates the installation of this part. 

Horizon Air concluded that a statement 

indicating the association with AD 

2021–25–12 would enhance the 

awareness of the compliance 

requirements. 

The FAA concurs with the 

commenter’s request. The actions 

required by AD 2021–25–12 only apply 

to airplanes that have installed pivot pin 

retention bolt P/N NAS6204–14D in the 

NLG assembly and therefore do not 

apply to those airplanes that do not 

have that pivot pin retention bolt 

installed. The modification required by 

paragraph (g) of this AD results in the 

installation of pivot pin retention bolt P/ 

N NAS6204–14D. After an operator has 

complied with this AD, the operator is 

then subject to AD 2021–25–12. As 

specified in paragraph (g) of AD 2021– 

25–12, the operator must revise the 

existing maintenance or inspection 

program ‘‘. . . within 30 days after the 

installation of pivot pin retention bolt 

part number P/N NAS6204–14D. . . .’’ 

As specified in paragraph (i) of AD 

2021–25–12, repetitive lubrications of 

the part are required at intervals not to 

exceed 400 flight cycles. The FAA has 

added Note 1 to paragraph (g) of this AD 

to refer to AD 2021–25–12 after 

installing pivot pin retention bolt P/N 

NAS6204–14D. 

Conclusion 

The FAA reviewed the relevant data, 

considered the comments received, and 

determined that air safety requires 

adopting this AD as proposed. Except 

for minor editorial changes, and any 

other changes described previously, this 

AD is adopted as proposed in the 

NPRM. None of the changes will 

increase the economic burden on any 

operator. Accordingly, the FAA is 

issuing this AD to address the unsafe 

condition on these products. 

Related Service Information Under 1 

CFR Part 51 

De Havilland Aircraft of Canada 

Limited has issued Service Bulletin 84– 

32–161, Revision B, dated March 31, 


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Federal Register / Vol. 87, No. 107 / Friday, June 3, 2022 / Rules and Regulations 33629 

2021, including UTC Aerospace 

Systems Service Bulletin 47100–32–145, 

Revision 3, dated March 26, 2021. This 

service information describes 

procedures for modifying the NLG 

shock strut assembly by replacing 

special bolt, part number (P/N) 47205– 

1 or 47205–3, with a new retention bolt, 

P/N NAS6204–14D (the modification 

includes a reverse orientation of the 

retention bolt and a rework of the 

weight on wheel (WOW) proximity 

sensor cover to provide clearance for the 

re-oriented retention bolt). 

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. 

Difference Between This AD and the 

MCAI 

This AD only requires the 

modification specified in Part I of TCCA 

AD CF–2009–29R4. The other actions 

specified in TCCA AD CF–2009–29R4 

are required by FAA AD 2021–25–12. 

Costs of Compliance 

The FAA estimates that this AD 

affects 54 airplanes of U.S. registry. The 

FAA estimates the following costs to 

comply with this AD: 

ESTIMATED COSTS FOR REQUIRED ACTIONS

Labor cost Parts cost Cost per 

product 

Cost on U.S. 

operators 

4 work-hours × $85 per hour = $340 .......................................................................................... $8 $348 $18,792 

Authority for This Rulemaking 

Title 49 of the United States Code 

specifies the FAA’s authority to issue 

rules on aviation safety. Subtitle I, 

section 106, describes the authority of 

the FAA Administrator. Subtitle VII: 

Aviation Programs, describes in more 

detail the scope of the Agency’s 

authority. 

The FAA is issuing this rulemaking 

under the authority described in 

Subtitle VII, Part A, Subpart III, Section 

44701: General requirements. Under 

that section, Congress charges the FAA 

with promoting safe flight of civil 

aircraft in air commerce by prescribing 

regulations for practices, methods, and 

procedures the Administrator finds 

necessary for safety in air commerce. 

This regulation is within the scope of 

that authority because it addresses an 

unsafe condition that is likely to exist or 

develop on products identified in this 

rulemaking action. 

Regulatory Findings 

This AD will not have federalism 

implications under Executive Order 

13132. This AD will not have a 

substantial direct effect on the States, on 

the relationship between the national 

government and the States, or on the 

distribution of power and 

responsibilities among the various 

levels of government. 

For the reasons discussed above, I 

certify that this AD: 

(1) Is not a ‘‘significant regulatory 

action’’ under Executive Order 12866, 

(2) Will not affect intrastate aviation 

in Alaska, and 

(3) Will not have a significant 

economic impact, positive or negative, 

on a substantial number of small entities 

under the criteria of the Regulatory 

Flexibility Act. 

List of Subjects in 14 CFR Part 39 

Air transportation, Aircraft, Aviation 

safety, Incorporation by reference, 

Safety. 

The Amendment 

Accordingly, under the authority 

delegated to me by the Administrator, 

the FAA amends 14 CFR part 39 as 

follows: 

PART 39—AIRWORTHINESS 

DIRECTIVES 

■ 1. The authority citation for part 39 

continues to read as follows: 

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

§ 39.13 [Amended] 

■ 2. The FAA amends § 39.13 by adding 

the following new airworthiness 

directive: 

2022–11–11 De Havilland Aircraft of 

Canada Limited (Type Certificate 

Previously Held by Bombardier, Inc.): 

Amendment 39–22061; Docket No. 

FAA–2022–0143; Project Identifier 

MCAI–2021–01401–T. 

(a) Effective Date 

This airworthiness directive (AD) is 

effective July 8, 2022. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to De Havilland Aircraft 

of Canada Limited (type certificate 

previously held by Bombardier, Inc.) Model 

DHC–8–401 and –402 airplanes, certificated 

in any category, serial numbers 4001 and 

4003 and subsequent. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 32, Landing gear. 

(e) Unsafe Condition 

This AD was prompted by reports of a 

certain bolt at the pivot pin link being found 

missing or having stress corrosion cracking. 

The FAA is issuing this AD to address failure 

of the pivot pin retention bolt, which could 

result in a loss of directional control or loss 

of a nose landing gear (NLG) tire during 

takeoff or landing, which could lead to 

runway excursions. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Modification 

For any airplane having an NLG shock 

strut assembly, part number (P/N) 47100–XX 

(where XX represents any number), that has 

special bolt P/N 47205–1 or 47205–3: Within 

1,600 flight cycles or 9 months after the 

effective date of this AD, whichever occurs 

first, modify the NLG shock strut assembly, 

in accordance with paragraph 3.B., 

‘‘Procedure,’’ of the Accomplishment 

Instructions of De Havilland Aircraft of 

Canada Limited Service Bulletin 84–32–161, 

Revision B, dated March 31, 2021, including 

UTC Aerospace Systems Service Bulletin 

47100–32–145, Revision 3, dated March 26, 

2021. 

Note 1 to paragraph (g): After installing 

pivot pin retention bolt part number 

NAS6204–14D, AD 2021–25–12, Amendment 

39–21856 (86 FR 72174, December 21, 2021) 

applies to pivot pin retention bolt part 

number NAS6204–14D. 

(h) Credit for Previous Actions 

This paragraph provides credit for actions 

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

actions were performed before the effective 

date of this AD using De Havilland Aircraft 

of Canada Limited Service Bulletin 84–32– 

161, dated April 7, 2020, including UTC 

Aerospace Systems Service Bulletin 47100– 

32–145, dated April 3, 2020; or De Havilland 

Aircraft of Canada Limited Service Bulletin 

84–32–161, Revision A, dated January 27, 

2021, including UTC Aerospace Systems 

Service Bulletin 47100–32–145, Revision 2, 

dated January 4, 2021. 

(i) Other FAA AD Provisions 

The following provisions also apply to this 

AD: 


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33630 Federal Register / Vol. 87, No. 107 / Friday, June 3, 2022 / Rules and Regulations 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, New York 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 

responsible Flight Standards Office, as 

appropriate. If sending information directly 

to the manager of the certification office, 

send it to ATTN: Program Manager, 

Continuing Operational Safety, FAA, New 

York ACO Branch, 1600 Stewart Avenue, 

Suite 410, Westbury, NY 11590; telephone 

516–228–7300; fax 516–794–5531. 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, New York ACO Branch, 

FAA; or Transport Canada Civil Aviation 

(TCCA); or De Havilland Aircraft of Canada 

Limited’s TCCA Design Approval 

Organization (DAO). If approved by the DAO, 

the approval must include the DAOauthorized signature. 

(j) Related Information 

(1) Refer to Mandatory Continuing 

Airworthiness Information (MCAI) TCCA AD 

CF–2009–29R4, dated October 1, 2021, for 

related information. This MCAI may be 

found in the AD docket on the internet at 

https://www.regulations.gov by searching for 

and locating Docket No. FAA–2022–0143. 

(2) For more information about this AD, 

contact Antariksh Shetty, Aerospace 

Engineer, Airframe and Propulsion Section, 

FAA, New York ACO Branch, 1600 Stewart 

Avenue, Suite 410, Westbury, NY 11590; 

telephone 516–228–7300; fax 516–794–5531; 

email 9-avs-nyaco-cos@faa.gov. 

(3) Service information identified in this 

AD that is not incorporated by reference is 

available at the addresses specified in 

paragraphs (k)(3) and (4) of this AD. 

(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) De Havilland Aircraft of Canada Limited 

Service Bulletin 84–32–161, Revision B, 

dated March 31, 2021, including UTC 

Aerospace Systems Service Bulletin 47100– 

32–145, Revision 3, dated March 26, 2021. 

Note 2 to paragraph (k)(2)(i): De Havilland 

issued De Havilland Service Bulletin 84–32– 

161, Revision B, dated March 31, 2021, with 

UTC Aerospace Systems Service Bulletin 

47100–32–145, Revision 3, dated March 26, 

2021, attached as one ‘‘merged’’ file for the 

convenience of affected operators. 

(ii) [Reserved] 

(3) For service information identified in 

this AD, contact De Havilland Aircraft of 

Canada Limited, Q-Series Technical Help 

Desk, 123 Garratt Boulevard, Toronto, 

Ontario M3K 1Y5, Canada; telephone 416– 

375–4000; fax 416–375–4539; email thd@

dehavilland.com; internet https://

dehavilland.com. 

(4) 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. 

(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 fr.inspection@nara.gov, or go to: 

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

ibr-locations.html. 

Issued on May 17, 2022. 

Gaetano A. Sciortino, 

Deputy Director for Strategic Initiatives, 

Compliance & Airworthiness Division, 

Aircraft Certification Service. 

[FR Doc. 2022–11758 Filed 6–2–22; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2022–0294; Project 

Identifier MCAI–2021–00550–R; Amendment 

39–22057; AD 2022–11–07] 

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 all 

Airbus Helicopters Deutschland GmbH 

(AHD) Model MBB–BK117 A–1, MBB– 

BK117 A–3, MBB–BK117 A–4, MBB– 

BK117 B–1, MBB–BK117 B–2, MBB– 

BK117 C–1, MBB–BK117 C–2, and 

MBB–BK117 D–2 helicopters. This AD 

was prompted by the FAA’s 

determination that aging of the 

elastomeric material of certain tension 

torsion straps (TT-Straps), during the 

period since manufacturing date up to 

first flight on a helicopter, may affect its 

structural characteristics. This AD 

requires the replacement of certain TTStraps, implementation of storage life 

limits for TT-Straps, a prohibition on 

installing certain TT-Straps, and 

conditions for installation of certain 

other TT-Straps, as specified in a 

European Union Aviation Safety Agency 

(EASA) AD, which is incorporated by 

reference. The FAA is issuing this AD 

to address the unsafe condition on these 

products. 

DATES: This AD is effective July 8, 2022. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of July 8, 2022. 

ADDRESSES: For EASA material 

incorporated by reference (IBR) in this 

final rule, contact EASA, KonradAdenauer-Ufer 3, 50668 Cologne, 

Germany; telephone +49 221 8999 000; 

email ADs@easa.europa.eu; internet 

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

EASA material 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. It is also available in the AD 

docket at https://www.regulations.gov 

by searching for and locating Docket No. 

FAA–2022–0294. 

Examining the AD Docket 

You may examine the AD docket at 

https://www.regulations.gov by 

searching for and locating Docket No. 

FAA–2022–0294; 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 EASA AD, 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: 

Kristi Bradley, Program Manager, COS 

Program Management Section, 

Operational Safety Branch, Compliance 

& Airworthiness Division, FAA, 10101 

Hillwood Pkwy., Fort Worth, TX 76177; 

phone: (817) 222–5110; email: 

kristin.bradley@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Background 

EASA, which is the Technical Agent 

for the Member States of the European 

Union, has issued EASA AD 2021–0122, 

dated May 6, 2021 (EASA AD 2021– 

0122), to correct an unsafe condition for 

all Airbus Helicopters Deutschland 

GmbH (AHD) (formerly Eurocopter 

Deutschland GmbH, Eurocopter 

Hubschrauber GmbH, MesserschmittBo ̈lkow-Blohm GmbH; Airbus 

Helicopters Inc., formerly American 

Eurocopter LLC) Model MBB–BK117 A– 

1, MBB–BK117 A–3, MBB–BK117 A–4, 

MBB–BK117 B–1, MBB–BK117 B–2, 


khammond on DSKJM1Z7X2PROD with RULES