38220 Federal Register / Vol. 86, No. 136 / Tuesday, July 20, 2021 / Rules and Regulations 

(a) Effective Date 

This airworthiness directive (AD) is 

effective August 24, 2021. 

(b) Affected ADs 

This AD replaces AD 2011–18–52, 

Amendment 39–17020 (77 FR 23109, April 

18, 2012) (AD 2011–18–52). 

(c) Applicability 

This AD applies to Leonardo S.p.a. (type 

certificate previously held by Agusta S.p.A.) 

Model AB139 and AW139 helicopters, 

certificated in any category, with tail rotor 

(T/R) blade, part number (P/N) 

3G6410A00131, 3G6410A00132, 

3G6410A00133, 4G6410A00131, 

4G6410A00132, or 4G6410A00133, installed. 

(d) Subject 

Joint Aircraft Service Component (JASC) 

Code: 6410, Tail Rotor Blades. 

(e) Unsafe Condition 

This AD defines the unsafe condition as a 

crack in a T/R blade. This condition could 

result in failure of a T/R blade and 

subsequent loss of control of the helicopter. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Required Actions 

(1) For T/R blade P/Ns 3G6410A00131 and 

4G6410A00131, within 5 hours time-inservice (TIS) after May 3, 2012 (the effective 

date of AD 2011–18–52), establish a life limit 

of 600 hours TIS or 1,500 takeoff and landing 

cycles (cycles), whichever occurs first, on the 

affected T/R blades and update the 

helicopter’s historical records. If a T/R 

blade’s total number of cycles is unknown, 

determine the T/R blade cycles by 

multiplying the T/R blade’s hours TIS by 4. 

(2) For T/R blade P/Ns 3G6410A00131 and 

4G6410A00131, thereafter following 

paragraph (g)(1) of this AD, remove any T/R 

blade from service before accumulating 600 

total hours TIS or 1,500 total cycles, 

whichever occurs first. 

(3) For T/R blade P/Ns 3G6410A00132, 

3G6410A00133, 4G6410A00132, and 

4G6410A00133, within 5 hours TIS after the 

effective date of this AD, determine the total 

number of cycles. If a T/R blade’s total 

number of cycles is unknown, determine the 

T/R blade cycles by multiplying the blade’s 

hours TIS by 4. Before further flight, remove 

any T/R blade from service that has 

accumulated or exceeded its life limit as 

follows. Thereafter, remove any T/R blade 

from service before accumulating its life limit 

as follows: 

(i) T/R blade P/Ns 3G6410A00132 and 

4G6410A00132: 1,200 total hours TIS or 

3,200 total cycles, whichever occurs first. 

(ii) T/R blade P/N 3G6410A00133: 40,000 

total cycles. 

(iii) T/R blade P/N 4G6410A00133: 4,033 

total hours TIS or 40,000 cycles, whichever 

occurs first. 

Note 1 to paragraph (g)(3): A combination 

of T/R blades having different P/Ns can be 

installed on the same helicopter. The eligible 

combinations of T/R blades P/N are listed in 

AgustaWestland Mandatory Bollettino 

Tecnico No. 139–265, Revision B, dated 

February 18, 2014 (BT No. 139–265). 

(4) For T/R blade P/Ns 3G6410A00131 and 

P/N 4G6410A00131, within 25 hours TIS 

after the effective date of this AD, and 

thereafter at intervals not to exceed 25 hours 

TIS, visually inspect the T/R blade for a crack 

and damage that exceeds allowable limits. 

Inspect in the area depicted in Figure 1 of BT 

No. 139–265 using a mirror, a 5X or higher 

power magnifying glass, and a flashlight, or 

borescope. If there is a crack or damage that 

exceeds allowable limits, before further 

flight, remove the T/R blade from service. 

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

not install on any helicopter any T/R blade 

P/N 3G6410A00131 or P/N 4G6410A00131, 

unless the actions required by paragraphs 

(g)(1), (2), and (4) of this AD have been 

accomplished. 

(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 Aviation Safety Agency (now 

European Union Aviation Safety Agency) 

(EASA) AD 2012–0076R2, dated February 20, 

2014. You may view the EASA AD at https:// 

www.regulations.gov in Docket No. FAA– 

2021–0348. 

(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) AgustaWestland Mandatory Bollettino 

Tecnico No. 139–265, Revision B, dated 

February 18, 2014. 

(ii) [Reserved] 

(3) For service information identified in 

this AD, contact Leonardo S.p.A. Helicopters, 

Emanuele Bufano, Head of Airworthiness, 

Viale G.Agusta 520, 21017 C. Costa di 

Samarate (Va) Italy; telephone +39–0331– 

225074; fax +39–0331–229046; or at https:// 

www.leonardocompany.com/en/home. 

(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 July 2, 2021. 

Gaetano A. Sciortino, 

Deputy Director for Strategic Initiatives, 

Compliance & Airworthiness Division, 

Aircraft Certification Service. 

[FR Doc. 2021–15303 Filed 7–19–21; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2021–0175; Project 

Identifier 2001–SW–33–AD; Amendment 39– 

21643; AD 2021–14–16] 

RIN 2120–AA64 

Airworthiness Directives; Airbus 

Helicopters (Type Certificate 

Previously Held by Eurocopter France) 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: The FAA is adopting a new 

airworthiness directive (AD) for all 

Airbus Helicopters (type certificate 

previously held by Eurocopter France) 

Model SA–365N, SA–365N1, AS– 

365N2, AS 365 N3, and SA–366G1 

helicopters. This AD was prompted by 

a quality control check that revealed 

some stretcher attachment holes were 

improperly located on the frame where 

there was insufficient edge distance. 

This AD requires measuring the 9- 

degree frame flange (frame) for the 

correct edge distance of the four 

attachment holes for the stretcher 

support and inspecting for cracks, and 

repairing the frame, if necessary, and 

installation of a reinforcement plate 

(reinforcing angle), as specified in two 

Direction Ge ́ne ́rale de l’Aviation Civile 

(DGAC) ADs, which are incorporated by 

reference. The FAA is issuing this AD 

to address the unsafe condition on these 

products. 

DATES: This AD is effective August 24, 

2021. 


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Federal Register / Vol. 86, No. 136 / Tuesday, July 20, 2021 / Rules and Regulations 38221 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in this AD 

as of August 24, 2021. 

ADDRESSES: For DGAC material 

incorporated by reference (IBR) in this 

AD, contact the European Union 

Aviation Safety Agency (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 the DGAC material on the EASA 

website at https://ad.easa.europa.eu. 

For American Eurocopter material, 

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 DGAC and American Eurocopter 

material at the FAA, Office of the 

Regional Counsel, Southwest Region, 

10101 Hillwood Pkwy., Room 6N–321, 

Fort Worth, TX 76177. Service 

information that is incorporated by 

reference is also available at https://

www.regulations.gov by searching for 

and locating Docket No. FAA–2021– 

0175. 

Examining the AD Docket 

You may examine the AD docket at 

https://www.regulations.gov by 

searching for and locating Docket No. 

FAA–2021–0175; 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 DGAC ADs, 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: 

Blaine Williams, Aerospace Engineer, 

Cabin Safety & Environmental Systems 

Section, Los Angeles ACO Branch, 

Compliance & Airworthiness Division, 

3960 Paramount Blvd., Lakewood, CA 

90712; telephone 562–627–5371; email 

blaine.williams@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Background 

The DGAC, which was the Technical 

Agent for France, issued DGAC AD 

2001–061–053(A), dated February 21, 

2001 (DGAC AD 2001–061–053(A)) for 

certain Model SA–365N, SA–365N1, 

AS–365N2, and AS 365 N3 helicopters; 

and DGAC AD 2001–283–025(A), dated 

July 11, 2001 (DGAC AD 2001–283– 

025(A)) for all Model SA–366G1 

helicopters (also referred to as the 

Mandatory Continuing Airworthiness 

Information, or the MCAI), to correct an 

unsafe condition for those helicopters. 

The FAA issued a second 

supplemental notice of proposed 

rulemaking (SNPRM) to amend 14 CFR 

part 39 by adding an AD that would 

apply to all Airbus Helicopters (type 

certificate previously held by 

Eurocopter France) Model SA–365N, 

SA–365N1, AS–365N2, AS 365 N3, and 

SA–366G1 helicopters. The second 

SNPRM published in the Federal 

Register on May 7, 2021 (86 FR 24556). 

The second SNPRM proposed to require 

inspecting the frame for the correct edge 

distance of the four attachment holes of 

the stretcher support and for a crack, 

and repairing the frame, if necessary, 

and installation of a reinforcement plate 

(reinforcing angle) on the frame, as 

specified in DGAC AD 2001–061– 

053(A) and DGAC AD 2001–283– 

025(A). The second SNPRM also 

included references to an engineering 

report that lists approved U.S. 

alternative fasteners and materials that 

may be used in any required repairs. 

The second SNPRM was issued because 

a significant amount of time elapsed 

since the first SNPRM was published. 

The FAA is issuing this AD to address 

failure of the 9-degree frame due to a 

crack at the stretcher support 

attachment holes, which could result in 

loss of a passenger door, damage to the 

rotor system, and subsequent loss of 

control of the helicopter. See the MCAI 

for additional background information. 

Discussion of Final Airworthiness 

Directive 

Comments 

The FAA received no comments on 

the second SNPRM or on the 

determination of the costs. 

Conclusion 

The FAA reviewed the relevant data 

and determined that air safety and the 

public interest require adopting this 

final rule as proposed, except for minor 

editorial changes. The FAA has 

determined that these minor changes: 

• Are consistent with the intent that 

was proposed in the second SNPRM for 

addressing the unsafe condition; and 

• Do not add any additional burden 

upon the public than was already 

proposed in the second SNPRM. 

Related Service Information Under 1 

CFR Part 51 

DGAC AD 2001–061–053(A) and 

DGAC AD 2001–283–025(A) describe 

procedures for measuring the edge 

distance of the webs at the four 

attachment holes of the stretcher 

support on the left and right sides of the 

9-degree frame, and additional actions 

depending on the findings. The 

additional actions include repetitively 

inspecting the frame for cracking, repair 

if necessary, and installation of a 

reinforcement plate (reinforcing angle) 

on the frame. These documents are 

distinct since they refer to different 

helicopter models. 

American Eurocopter Engineering 

Report No. AEC/03R–E–005, 

‘‘Addendum ASB 53.00.42 and 53.00.43 

AS365,’’ dated January 29, 2003, 

specifies U.S. and European rivet 

equivalent part numbers, U.S. rivet part 

numbers with acceptable substitute 

materials with greater strength 

properties, and 5 rivet, 6 rivet, and pin 

Hi-lok alternatives. 

This material is reasonably available 

because the interested parties have 

access to it through their normal course 

of business or by the means identified 

in the ADDRESSES section. 

Differences Between This AD and the 

MCAI 

The FAA has determined that 

acceptable U.S. alternatives to the 

fasteners and materials needed to 

perform repairs or modifications are 

listed in American Eurocopter 

Engineering Report No. AEC/03R–E–005 

‘‘Addendum ASB 53.00.42 and 

53.00.043 AS365’’, dated January 29, 

2003. 

Where DGAC AD 2001–061–053(A) 

exempts helicopters that were delivered 

after January 31, 2001, from the 

applicability, this AD does not exempt 

those helicopters. 

Costs of Compliance 

The FAA estimates that this AD 

affects 31 helicopters of U.S. registry. 

The FAA estimates the following costs 

to comply with this AD: 


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38222 Federal Register / Vol. 86, No. 136 / Tuesday, July 20, 2021 / Rules and Regulations 

ESTIMATED COSTS FOR REQUIRED ACTIONS

Labor cost Parts cost Cost per 

product 

Cost on U.S. 

operators 

3 work-hours × $85 per hour = $255 .......................................................................................... $100 $355 $11,005 

The FAA estimates the following 

costs to do any necessary on-condition 

actions that would be required based on 

the results of any required actions. The 

FAA has no way of determining the 

number of helicopters that might need 

these on-condition actions: 

ESTIMATED COSTS OF ON-CONDITION ACTION

Labor cost Parts cost Cost per 

product 

Up to 8 work-hours × $85 per hour = $680 ............................................................................................................ $250 Up to $930 

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. 

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: 

2021–14–16 Airbus Helicopters (Type 

Certificate Previously Held by 

Eurocopter France): Amendment 39– 

21643; Docket No. FAA–2021–0175; 

Project Identifier 2001–SW–33–AD. 

(a) Effective Date 

This airworthiness directive (AD) is 

effective August 24, 2021. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to all Airbus Helicopters 

(type certificate previously held by 

Eurocopter France) Model SA–365N, SA– 

365N1, AS–365N2, AS 365 N3, and SA– 

366G1 helicopters, certificated in any 

category. 

(d) Subject 

Joint Aircraft Service Component (JASC) 

Code 5311, Fuselage Main, Frame. 

(e) Reason 

This AD was prompted by a quality control 

check that revealed some stretcher 

attachment holes were improperly located on 

the frame where there was insufficient edge 

distance. The FAA is issuing this AD to 

address failure of the 9-degree frame flange 

(frame) due to a crack at the stretcher support 

attachment holes, which could result in loss 

of a passenger door, damage to the rotor 

system, and subsequent loss of control of the 

helicopter. 

(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 the applicable Direction 

Ge ́ne ́rale de l’Aviation Civile (DGAC) ADs 

specified in paragraphs (g)(1) and (2) of this 

AD. 

(1) For Model SA–365N, SA–365N1, AS– 

365N2, and AS 365 N3 helicopters: DGAC 

AD 2001–061–053(A), dated February 21, 

2001, (DGAC AD 2001–061–053(A)). 

(2) For Model SA–366G1 helicopters: 

DGAC AD 2001–283–025(A), dated July 11, 

2001 (DGAC AD 2001–283–025(A)). 

(h) Exceptions to DGAC AD 2001–061– 

053(A) and DGAC AD 2001–283–025(A) 

(1) Where paragraph 3.1 of DGAC AD 

2001–061–053(A) and DGAC AD 2001–283– 

025(A) specifies an initial compliance time to 

do the measurement, for this AD, do the 

measurement within 50 hours time-in-service 

(TIS) after the effective date of this AD. 

(2) Where paragraph 3.1. of DGAC AD 

2001–061–053(A) and DGAC AD 2001–283– 

025(A) specifies to do a measurement, for 

this AD, do an inspection of the area around 

the attachment holes for cracks concurrently 

with the measurement. 

(3) Where paragraph 3.2.1.a) of DGAC AD 

2001–061–053(A) and DGAC AD 2001–283– 

025(A) specifies ‘‘every 550 flight hours, 

check that there is no crack in the flange,’’ 

for this AD, inspect (check) the area around 

the attachment holes for cracks at intervals 

not to exceed 550 hours TIS. 

(4) Where paragraph 3.2.1.b) of DGAC AD 

2001–061–053(A) and DGAC AD 2001–283– 

025(A) requires installation of a 

reinforcement plate (reinforcing angle) on the 

flange for certain helicopters, do the 


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installation within 550 hours TIS after 

accomplishment of the measurement 

specified in paragraph 3.1. of DGAC AD 

2001–061–053(A) and DGAC AD 2001–283– 

025(A). 

(5) Where the service information referred 

to in DGAC AD 2001–061–053(A) and DGAC 

AD 2001–283–025(A) specifies to perform a 

dye penetrant crack inspection ‘‘if in doubt,’’ 

this AD requires performing a dye penetrant 

inspection. 

(6) Where paragraph 3.2.2. of DGAC AD 

2001–061–053(A) and DGAC AD 2001–283– 

025(A) specifies to do various actions 

specified in paragraphs 3.2.2.a), b), and c) of 

those ADs, for this AD, if any frame is 

cracked, before further flight, repair the 

frame. Acceptable U.S. alternatives to the 

fasteners and materials needed to perform 

repairs or modifications are listed in 

American Eurocopter Engineering Report No. 

AEC/03R–E–005, ‘‘Addendum ASB 53.00.42 

and 53.00.43 AS365’’, dated January 29, 

2003. 

(7) Where the Note in paragraph 3.2.2. of 

DGAC AD 2001–061–053(A) and DGAC AD 

2001–283–025(A) specifies the instructions 

are no longer applicable after a customized 

repair has been carried out, for this AD, 

modifying or repairing the frame constitutes 

terminating action for the requirements of 

this AD. 

(i) Special Flight Permit 

Special flight permits, as described in 14 

CFR 21.197 and 21.199, are prohibited. 

(j) 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 (k) 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. 

(k) Related Information 

For more information about this AD, 

contact Blaine Williams, Aerospace Engineer, 

Cabin Safety & Environmental Systems 

Section, Los Angeles ACO Branch, 

Compliance & Airworthiness Division, 3960 

Paramount Blvd., Lakewood, CA 90712; 

telephone 562–627–5371; email 

blaine.williams@faa.gov. 

(l) 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) Direction Ge ́ne ́rale de l’Aviation Civile 

(DGAC) AD 2001–061–053(A), dated 

February 21, 2001. 

(ii) DGAC AD 2001–283–025(A), dated July 

11, 2001. 

(iii) American Eurocopter Engineering 

Report No. AEC/03R–E–005, ‘‘Addendum 

ASB 53.00.42 and 53.00.43 AS365’’, dated 

January 29, 2003. 

(3) For DGAC AD 2001–061–053(A) and 

DGAC AD 2001–283–025(A), contact the 

European Union Aviation Safety Agency 

(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 these 

DGAC ADs on the EASA website at https:// 

ad.easa.europa.eu. 

(4) For American Eurocopter material 

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. 

(5) 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. 

(6) 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 July 2, 2021. 

Ross Landes, 

Deputy Director for Regulatory Operations, 

Compliance & Airworthiness Division, 

Aircraft Certification Service. 

[FR Doc. 2021–15302 Filed 7–19–21; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2021–0031; Project 

Identifier MCAI–2020–01420–T; Amendment 

39–21625; AD 2021–13–20] 

RIN 2120–AA64 

Airworthiness Directives; Airbus 

Canada Limited Partnership (Type 

Certificate Previously Held by C Series 

Aircraft Limited Partnership (CSALP); 

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 

Airbus Canada Limited Partnership 

Model BD–500–1A10 and BD–500– 

1A11 airplanes. This AD was prompted 

by reports of corrosion on the waste box, 

waste access doubler, and waste service 

door of the rear fuselage due to 

contamination from waste valve leakage. 

This AD requires an inspection for 

corrosion of the waste box, waste access 

doubler, and waste service door, and 

corrective actions if necessary, as 

specified in a Transport Canada Civil 

Aviation (TCCA) 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 August 24, 

2021. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of August 24, 2021. 

ADDRESSES: For material incorporated 

by reference (IBR) in this AD, contact 

TCCA, Transport Canada National 

Aircraft Certification, 159 Cleopatra 

Drive, Nepean, Ontario, K1A 0N5, 

Canada; telephone 888–663–3639; email 

AD-CN@tc.gc.ca; internet https://

tc.canada.ca/en/aviation. You may view 

this IBR material at the FAA, 

Airworthiness Products Section, 

Operational Safety Branch, 2200 South 

216th St., Des Moines, WA. For 

information on the availability of this 

material at the FAA, call 206–231–3195. 

It is also available in the AD docket on 

the internet at https://

www.regulations.gov by searching for 

and locating Docket No. FAA–2021– 

0031. 

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– 

0031; 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: 

Siddeeq Bacchus, Aerospace Engineer, 

Mechanical Systems and Administrative 

Services Section, FAA, New York ACO 

Branch, 1600 Stewart Avenue, Suite 

410, Westbury, NY 11590; telephone 

516–228–7362; fax 516–794–5531; email 

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

SUPPLEMENTARY INFORMATION: 


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