30756 Federal Register / Vol. 86, No. 110 / Thursday, June 10, 2021 / Rules and Regulations 

(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 2021–0128, dated May 17, 2021. 

(ii) [Reserved] 

(3) For EASA AD 2021–0128, 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 at https://

www.regulations.gov by searching for and 

locating Docket No. FAA–2021–0458. 

(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 June 6, 2021. 

Lance T. Gant, 

Director, Compliance & Airworthiness 

Division, Aircraft Certification Service. 

[FR Doc. 2021–12301 Filed 6–8–21; 4:15 pm] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2020–0881; Project 

Identifier 2018–CE–024–AD; Amendment 

39–21578; AD 2021–11–16] 

RIN 2120–AA64 

Airworthiness Directives; Piper 

Aircraft, Inc. Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: The FAA is superseding 

Airworthiness Directive (AD) 79–01–03, 

which applied to certain Piper Aircraft, 

Inc. (Piper) Model PA–36–285 airplanes, 

and AD 83–20–03, which applied to 

Piper Models PA–36–285, PA–36–300, 

and PA–36–375 airplanes. AD 79–01–03 

required repetitive inspections of the 

spar carry through assembly until 

replaced with a different part numbered 

spar carry through assembly. AD 83–20– 

03 established life limits for the wing 

spar structural components. This AD 

retains the requirements in AD 79–01– 

03 and AD 83–20–03 and requires the 

spar carry through assembly inspection 

from AD 79–01–03 for additional 

airplanes and adds life limits for certain 

wing structural components previously 

omitted from AD 83–20–03 for certain 

serial numbered airplanes. The FAA is 

issuing this AD to address the unsafe 

condition on these products. 

DATES: This AD is effective July 15, 

2021. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in this AD 

as of July 15, 2021. 

ADDRESSES: For service information 

identified in this final rule, contact 

Piper Aircraft, Inc., 2926 Piper Drive, 

Vero Beach, FL 32960; phone: (772) 

567–4361; website: https://

www.piper.com. You may view this 

service information at the FAA, 

Airworthiness Products Section, 

Operational Safety Branch, 901 Locust, 

Kansas City, MO 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–2020–0881. 

Examining the AD Docket 

You may examine the AD docket at 

https://www.regulations.gov by 

searching for and locating Docket No. 

FAA–2020–0881; 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: Dan 

McCully, Aviation Safety Engineer, 

FAA, Atlanta ACO Branch, 1701 

Columbia Avenue, College Park, GA 

30337; phone: (404) 474–5548; fax: (404) 

474–5606; email: william.mccully@

faa.gov. 

SUPPLEMENTARY INFORMATION: 

Background 

The FAA issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to supersede AD 79–01–03, 

Amendment 39–3383 (44 FR 36, January 

2, 1979), Docket No. 78–EA–69 (AD 79– 

01–03) and AD 83–20–03, Amendment 

39–4739 (48 FR 45535, October 6, 1983), 

Docket No. 83–CE–23–AD (AD 83–20– 

03). AD 79–01–03 applied to certain 

Piper Model PA–36–285 airplanes and 

required repetitive inspections of spar 

carry through assembly part number 

(P/N) 97370–00, with repair as 

necessary, until the spar carry through 

assembly is replaced with P/N 76824– 

02. AD 83–20–03 applied to Piper 

Models PA–36–285, PA–36–300, and 

PA–36–375 airplanes and established 

life limits for certain wing structural 

components. 

The NPRM published in the Federal 

Register on March 23, 2021 (86 FR 

15439). The NPRM was prompted by 

inconsistencies between the two ADs 

and the airplanes’ type certificate. The 

FAA determined that the life limits for 

the spar carry through assembly, P/N 

97370–00 or 76824–02, were 

inadvertently omitted from AD 83–20– 

03 for certain airplanes. In the NPRM, 

the FAA proposed to add the life limit 

for the spar carry through assembly for 

Models PA–36–285 and PA–36–300 

airplanes, serial numbers 36–7660123 

through 36–8160023; and Model PA– 

36–375 airplanes, serial numbers 36– 

7802001 through 36–8302025. The FAA 

also determined the repetitive 

inspections of the spar carry through 

assembly required by AD 79–01–03 

should apply to both Model PA–36–285 

and Model PA–36–300 airplanes until 

the life limit replacement of the spar 

carry through assembly with P/N 

76824–02. In the NPRM, the FAA also 

proposed to require adding the 

repetitive inspections for the Model PA– 

36–300 airplanes. After the initial life 

limit replacement of the wing spar carry 

through assembly, P/N 97370–00 with 

P/N 76824–02, the repetitive 

inspections will no longer be required. 

The FAA is issuing this AD to address 

the unsafe condition on these products. 

Discussion of Final Airworthiness 

Directive 

Comments 

The FAA received no comments on 

the NPRM or on the determination of 

the costs. 

Conclusion 

The FAA reviewed the relevant data 

and determined that air safety requires 

adoption of the AD as proposed. 

Accordingly, the FAA is issuing this AD 

to address the unsafe condition on these 

products. This AD is adopted as 

proposed in the NPRM. 

Related Service Information Under 1 

CFR Part 51 

The FAA reviewed Piper Service 

Bulletin No. 552A, dated August 3, 2018 

(Piper SB No. 552A); Piper Aircraft PA– 

36, Pawnee Brave Kit 764–394, Right 

Wing Main Spar Caps Replacement, 

dated June 9, 2012 (Piper Kit 764–394); 

and Piper Aircraft PA–36, Pawnee Brave 


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Federal Register / Vol. 86, No. 110 / Thursday, June 10, 2021 / Rules and Regulations 30757 

Kit 764–393, Left Wing Main Spar Caps 

Replacement, dated June 9, 2012 (Piper 

Kit 764–393). Piper SB No. 552A applies 

to Models PA–36–285 and PA–36–300 

airplanes and contains procedures for 

repetitively inspecting wing spar carry 

through assembly P/N 97370–00. Piper 

Kit 764–394 identifies the applicable 

parts and specifies procedures for 

replacing the right wing main spar caps, 

which includes the attachment bolts 

and wing carry through spar fittings and 

assembly. Piper Kit 764–393 identifies 

the applicable parts and specifies 

procedures for replacing the left wing 

main spar caps, which includes the 

attachment bolts and wing carry through 

spar fittings and assembly. 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 ADDRESSES. 

Other Related Service Information 

The FAA also reviewed Piper Aircraft 

Corporation Service Bulletin No. 552, 

dated February 3, 1978 (Piper SB No. 

552). Piper SB No. 552 contains the 

same procedures as Piper SB No. 552A, 

but Piper SB No. 552 only applies to 

Model PA–36–285 airplanes. 

Costs of Compliance 

The FAA estimates that this AD will 

affect 123 airplanes of U.S. registry. 

The FAA estimates the following 

costs to comply with this AD: 

ESTIMATED COSTS

Action Labor cost Parts cost Cost per 

product 

Cost on U.S. 

operators 

Inspection of P/N 97370–00 wing spar 

carry through assembly.

8 work-hours × $85 per hour = $680 ..... Not applicable ................ $680 $83,640 

Replacement of the wing attachment 

upper bolt and lower bolt.

10 work-hours × $85 per hour = $850 ... $1,310 (both bolts) ......... 2,160 265,680 

Replacement of wing carry through spar 

assembly *.

30 work-hours × $85 per hour = $2,550 $23,467 .......................... 26,017 3,200,091 

Replacement of Piper Kit 764–393 (Left) 

and Piper Kit 764–394 (Right) **.

20 work-hours × $85 per hour = $1,700 $26,867 (both kits) ......... 28,567 3,513,741 

* The wing carry through spar fitting, P/N 97713–03, is included in the wing carry through spar assembly, P/N 76824–02. 

** The replacement for the wing spar fitting P/N 97712–00 and the replacement for spar assembly P/Ns 97701–00 and 97701–01 are included 

in Piper Kit 764–393 and Piper Kit 764–394. 

Authority for This Rulemaking 

Title 49 of the United States Code 

specifies the FAA’s authority to issue 

rules on aviation safety. Subtitle I, 

Section 106, describes the authority of 

the FAA Administrator. Subtitle VII, 

Aviation Programs, describes in more 

detail the scope of the Agency’s 

authority. 

The FAA is issuing this rulemaking 

under the authority described in 

Subtitle VII, Part A, Subpart III, Section 

44701, General requirements. Under 

that section, Congress charges the FAA 

with promoting safe flight of civil 

aircraft in air commerce by prescribing 

regulations for practices, methods, and 

procedures the Administrator finds 

necessary for safety in air commerce. 

This regulation is within the scope of 

that authority because it addresses an 

unsafe condition that is likely to exist or 

develop on products identified in this 

rulemaking action. 

Regulatory Findings 

The FAA has determined that 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 to the extent that it justifies 

making a regulatory distinction, 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: 

■ a. Removing Airworthiness Directive 

79–01–03, Amendment 39–3383 (44 FR 

36, January 2, 1979), Docket No. 78–EA– 

69; and Airworthiness Directive 83–20– 

03, Amendment 39–4739 (48 FR 45535, 

October 6, 1983), Docket No. 83–CE–23– 

AD; and 

■ b. Adding the following new 

airworthiness directive: 

2021–11–16 Piper Aircraft, Inc.: 

Amendment 39–21578; Docket No. 

FAA–2020–0881; Project Identifier 

2018–CE–024–AD. 

(a) Effective Date 

This airworthiness directive (AD) is 

effective July 15, 2021. 

(b) Affected ADs 

This AD replaces AD 79–01–03, 

Amendment 39–3383 (44 FR 36, January 2, 

1979) (AD 79–01–03); and AD 83–20–03, 

Amendment 39–4739 (48 FR 45535, October 

6, 1983) (AD 83–20–03). 

(c) Applicability 

This AD applies to Piper Aircraft, Inc. 

Models PA–36–285, PA–36–300, and PA–36– 

375 airplanes, certificated in any category. 

(d) Subject 

Joint Aircraft System Component (JASC) 

Code 5700, Wings. 

(e) Unsafe Condition 

This AD was prompted by a review of AD 

83–20–03 and AD 79–01–03 and the 

determination that the requirements of those 

ADs did not address all of the affected 

airplanes. The FAA is issuing this AD to 

prevent fatigue damage to the wing structural 

components. The unsafe condition, if not 

addressed, could result in failure of the wing 

structure with consequent loss of control. 


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30758 Federal Register / Vol. 86, No. 110 / Thursday, June 10, 2021 / Rules and Regulations 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Inspection of the Wing Spar Carry 

Through Assembly 

(1) For Models PA–36–285 and PA–36–300 

airplanes, serial numbers 36–7360001 

through 36–7560003, with a wing spar carry 

through assembly part number (P/N) 97370– 

00 installed, before the airplane accumulates 

a total of 2,000 hours time-in-service (TIS) or 

within 25 hours TIS after the effective date 

of this AD, whichever occurs later, and 

thereafter at intervals not to exceed 100 hours 

TIS, inspect the wing spar carry through 

assembly by following the Instructions, 

section 1, of Piper Service Bulletin No. 552A, 

dated August 3, 2018, (Piper SB No. 552A). 

(2) If any damage is found during any 

inspection required by paragraph (g)(1) of 

this AD, before further flight, repair or 

replace the wing spar carry through assembly 

by following the Instructions, section 2, of 

Piper SB No. 552A. 

(3) Replacing wing spar carry through 

assembly P/N 97370–00 with wing spar carry 

through assembly P/N 76824–02 terminates 

the repetitive inspections required by 

paragraph (g)(1) of this AD. 

(h) Life Limit Replacement of Wing 

Structural Components 

Remove from service the wing structural 

components specified in paragraphs (h)(1) 

through (8) of this AD before the part 

accumulates the life limit hours TIS set forth 

in table 1 to paragraph (h) of this AD. If, on 

the effective date of this AD, the component 

will reach its life limit within 100 hours TIS 

or has already reached its life limit, remove 

the part from service within 100 hours TIS 

after the effective date of this AD. 

BILLING CODE 4910–13–P 

BILLING CODE 4910–13–C 

(1) Remove from service wing attachment 

upper bolt P/N 77245–00 and replace with an 

unused (zero hours TIS) wing attachment 

upper bolt P/N 77245–00. 

(2) Remove from service any wing carry 

through spar fitting P/Ns 97713–00, 97713– 

02, or 97713–03 and replace with an unused 

(zero hours TIS) wing carry through spar 

fitting P/N 97713–03. 

Note 1 to paragraph (h)(2): Wing carry 

through spar fitting P/N 97713–03 is 

included as part of spar carry through 

assembly P/N 76824–02. 

(3) Remove from service wing spar fitting 

P/N 97712–00 and replace with an unused 

(zero hours TIS) wing spar fitting P/N 97712– 

00 by following steps D(1)(a) through D(1)(c) 

or section D(2), in Piper Aircraft PA–36, 

Pawnee Brave Kit 764–393, Left Wing Main 

Spar Caps Replacement, dated June 9, 2012 

(Piper Kit 764–393), or Piper Aircraft PA–36, 

Pawnee Brave Kit 764–394, Right Wing Main 


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Table 1 to paragraph (h)-----Compliance Times/or Life Limit Replacement of Wing 

Com onents 

Airplanes Type of Paragraph of this AD 

Replacement 

(h)(l) (h)( 4) (h)(5) (h)(6) (h)(7) (h)(8) 

(h)(2) 

(h)(3) 

Models PA-36-285 and Life Limit Hours Time-in-Service on the 

PA-36-300 Component 

Serial Numbers Initial 4,100 4,100 NIA NIA 3,100 2,000 

(S/Ns) 36-7360001 Repetitive 4,100 4,100 NIA NIA 4,100 2,000 through 36-7560003 

S/Ns 36-7560004 Initial 4,100 NIA NIA 4,000 3,100 2,000 

through 36-7560055 Repetitive 4,100 NIA NIA 4,100 4,100 2,000 

S/Ns 36-7560056 Initial 4,100 NIA 4,100 4,000 NIA 2,000 

through 36-7660122 Repetitive 4,100 NIA 4,100 4,100 NIA 2,000 

S/Ns 36-7660123 Initial 4,100 4,100 4,100 NIA NIA 2,000 

through 36-8160023 Repetitive 4,100 4,100 4,100 NIA NIA 2,000 

Model PA-36-375 Life Limit Hours Time-in-Service on the 

Component 

(h)(l) (h)( 4) (h)(5) (h)(6) (h)(7) (h)(8) 

(h)(2) 

(h)(3) 

S/Ns 36-7802001 Initial 4,100 4,100 4,100 NIA NIA 2,000 

through 36-8302025 Repetitive 4,100 4,100 4,100 NIA NIA 2,000 
Federal Register / Vol. 86, No. 110 / Thursday, June 10, 2021 / Rules and Regulations 30759 

Spar Caps Replacement, dated June 9, 2012 

(Piper Kit 764–394), as applicable. 

Note 2 to paragraphs (h)(3): This note 

applies to paragraphs (h)(3) and (7) of this 

AD. Replacement parts for the left and right 

wing spar fittings P/N 97712–00 and the 

right, left, top, and bottom spar assemblies P/ 

Ns 97701–00 and 97701–01 are included 

with Piper Kit 764–393 and Piper Kit 764– 

394. 

(4) Remove from service spar carry through 

assembly P/N 97370–00 or 76824–02, as 

applicable, and replace with an unused (zero 

hours TIS) spar carry through assembly P/N 

76824–02. 

(5) Remove from service spar assembly P/ 

Ns 97701–00 and 97701–01, Revision P or 

later revision, and replace with an unused 

(zero hours TIS) spar assembly by following 

the Instructions, sections B. and C., in Piper 

Kit 764–393 or Piper Kit 764–394, as 

applicable. 

(6) Remove from service any spar carry 

through assembly P/N 76767–00 or P/N 

76824–02 and replace with an unused (zero 

hours TIS) spar carry through assembly P/N 

76824–02. 

(7) Remove from service spar assemblies P/ 

Ns 97701–00 and 97701–01, Revision N or 

earlier revision, and replace with an unused 

(zero hours TIS) left spar cap replacement kit 

P/N 764–393 and right spar cap replacement 

kit P/N 764–394 by following the 

Instructions, sections B. and C., in Piper Kit 

764–393 or Piper Kit 764–394, as applicable. 

(8) Remove from service wing attachment 

lower bolt P/N 77245–00 and replace with an 

unused (zero hours TIS) P/N 77245–00 bolt. 

(i) Credit for Previous Actions 

You may take credit for the actions 

required by paragraph (g) of this AD if you 

performed those actions before the effective 

date of this AD using Piper Aircraft 

Corporation Service Bulletin No. 552, dated 

February 3, 1978. 

(j) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Atlanta 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 local Flight Standards 

District Office, as appropriate. If sending 

information directly to the manager of the 

certification office, send it to the attention of 

the person identified in Related Information. 

(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. 

(3) AMOCs approved for AD 79–01–03 and 

AD 83–20–03 are approved as AMOCs for the 

corresponding provisions of this AD. 

(k) Related Information 

For more information about this AD, 

contact Dan McCully, Aviation Safety 

Engineer, FAA, Atlanta ACO Branch, 1701 

Columbia Avenue, College Park, GA 30337; 

phone: (404) 474–5548; fax: (404) 474–5606; 

email: william.mccully@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) Piper Service Bulletin No. 552A, dated 

August 3, 2018; 

(ii) Piper Aircraft PA–36, Pawnee Brave Kit 

764–394, Right Wing Main Spar Caps 

Replacement, dated June 9, 2012; and 

Note 3 to paragraph (l)(2)(ii): The Kit List 

and Sketch A for Piper Aircraft PA–36, 

Pawnee Brave Kit 764–394, Right Wing Main 

Spar Caps Replacement, dated June 9, 2012; 

and Piper Aircraft PA–36, Pawnee Brave Kit 

764–393, Left Wing Main Spar Caps 

Replacement, dated June 9, 2012, were 

revised and dated June 9, 2012. The 

instructions and sketches in the rest of the 

documents were reformatted but retain the 

previous date of March 30, 1982, because the 

content of those pages was unchanged. 

(iii) Piper Aircraft PA–36, Pawnee Brave 

Kit 764–393, Left Wing Main Spar Caps 

Replacement, dated June 9, 2012. 

(3) For service information identified in 

this AD, contact Piper Aircraft, Inc., 2926 

Piper Drive, Vero Beach, FL 32960; phone: 

(772) 567–4361; website: www.piper.com. 

(4) You may view this service information 

at FAA, Policy and Innovation Division, 901 

Locust, Kansas City, MO 64106. For 

information on the availability of this 

material at the FAA, call (816) 329–4148. 

(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 19, 2021. 

Lance T. Gant, 

Director, Compliance & Airworthiness 

Division, Aircraft Certification Service. 

[FR Doc. 2021–12043 Filed 6–9–21; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2020–1183; Project 

Identifier 2019–SW–008–AD; Amendment 

39–21565; AD 2021–11–03] 

RIN 2120–AA64 

Airworthiness Directives; Airbus 

Helicopters 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: The FAA is adopting a new 

airworthiness directive (AD) for certain 

Airbus Helicopters Model EC 155B, 

EC155B1, SA–365N, SA–365N1, AS– 

365N2, and AS 365 N3 helicopters, as 

identified in a European Aviation Safety 

Agency (now European Union Aviation 

Safety Agency) (EASA) AD. This AD 

was prompted by a report of an in-flight 

loss of engine and main gearbox (MGB) 

cowlings. This AD requires inspecting 

the MGB fixed cowling front fitting 

(MGB front fitting), and depending on 

findings, corrective action. This AD also 

requires a new modification, which is a 

terminating action for the inspection, as 

specified in an 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 15, 

2021. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in this AD 

as of July 15, 2021. 

ADDRESSES: For EASA material 

incorporated by reference (IBR) in this 

AD, contact the 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 this 

material on the EASA website at https:// 

ad.easa.europa.eu. For Airbus 

Helicopters service information, contact 

Airbus Helicopters, 2701 N Forum 

Drive, Grand Prairie, TX 75052; 

telephone (972) 641–0000 or (800) 232– 

0323; fax (972) 641–3775; or at https:// 

www.airbus.com/helicopters/services/ 

technical-support.html. You may view 

this 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 on the 

internet at https://www.regulations.gov 

by searching for and locating Docket No. 

FAA–2020–1183. 

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– 

1183; 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. 


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