Federal Register / Vol. 86, No. 113 / Tuesday, June 15, 2021 / Rules and Regulations 31609 

recent inspection was performed as specified 

in AWL No. 47–AWL–06, whichever is latest. 

(12) For AWL No. 47–AWL–07, ‘‘Nitrogen 

Generation System (NGS)—Nitrogen 

Enriched Air (NEA) Distribution Ducting 

Integrity’’: Within 6,500 flight hours after the 

date of issuance of the original airworthiness 

certificate or the original export certificate of 

airworthiness, within 6,500 flight hours after 

accomplishment of the actions specified in 

Boeing Service Bulletin 737–47–1003, or 

within 6,500 flight hours after the most 

recent inspection was performed as specified 

in AWL No. 47–AWL–07, whichever is latest. 

(13) For AWL No. 47–AWL–09, ‘‘Nitrogen 

Generation System—Oxygen Sensor’’: Within 

18,000 flight hours after the date of issuance 

of the original airworthiness certificate or the 

original export certificate of airworthiness, or 

within 18,000 flight hours after the most 

recent replacement was performed as 

specified in AWL No. 47–AWL–09, or within 

36 months after the effective date of this AD, 

whichever is latest. 

(14) For AWL No. 28–AWL–101, ‘‘Engine 

Fuel Suction Feed Operational Test’’: Within 

7,500 flight hours or 36 months, whichever 

occurs first, after the date of issuance of the 

original airworthiness certificate or the 

original export certificate of airworthiness; or 

within 7,500 flight hours or 36 months, 

whichever occurs first, after the most recent 

inspection was performed as specified in 

AWL No. 28–AWL–101; whichever is later. 

(h) Additional Acceptable Exceptions to the 

AWLs 

As an option, when accomplishing the 

actions required by paragraph (g) of this AD, 

the changes specified in paragraphs (h)(1) 

through (3) of this AD are acceptable. 

(1) Where AWL No. 28–AWL–05 identifies 

wire types BMS 13–48, BMS 13–58, and BMS 

13–60, the following wire types are 

acceptable: MIL–W–22759/16, SAE 

AS22759/16 (M22759/16), MIL–W–22759/32, 

SAE AS22759/32 (M22759/32), MIL–W– 

22759/34, SAE AS22759/34 (M22759/34), 

MIL–W–22759/41, SAE AS22759/41 

(M22759/41), MIL–W–22759/86, SAE 

AS22759/86 (M22759/86), MIL–W–22759/87, 

SAE AS22759/87 (M22759/87), MIL–W– 

22759/92, and SAE AS22759/92 (M22759/ 

92); and MIL–C–27500 and NEMA WC 27500 

cables constructed from these military or 

SAE specification wire types, as applicable. 

(2) Where AWL No. 28–AWL–05 identifies 

TFE–2X Standard wall for wire sleeving, the 

following sleeving materials are acceptable: 

Roundit 2000NX and Varglas Type HO, HP, 

or HM. 

(3) Where AWL No. 28–AWL–20 specifies 

the operational test for left center tank fuel 

boost pump relay R54 and right center tank 

fuel boost pump relay R55, for airplanes that 

have complied with paragraph (g)(2)(ii) of AD 

2011–20–07, Amendment 39–16818 (76 FR 

60710, September 30, 2011), or that have 

installed Supplemental Type Certificate 

(STC) ST02076LA, that action does not 

apply. 

(i) No Alternative Actions, Intervals, or 

Critical Design Configuration Control 

Limitations (CDCCLs) 

Except as provided in paragraph (h) of this 

AD, after the existing maintenance or 

inspection program has been revised as 

required by paragraph (g) of this AD, no 

alternative actions (e.g., inspections), 

intervals, or CDCCLs may be used unless the 

actions, intervals, and CDCCLs are approved 

as an alternative method of compliance 

(AMOC) in accordance with the procedures 

specified in paragraph (k) of this AD. 

(j) Terminating Action for Certain AD 

Requirements 

Accomplishment of the revision required 

by paragraph (g) of this AD terminates the 

requirements specified in paragraphs (j)(1) 

through (7) of this AD for that airplane. 

(1) The revision required by the 

introductory text to paragraph (h) and 

paragraph (h)(1) of AD 2008–06–03. 

(2) All requirements of AD 2008–10–10 R1. 

(3) The revision required by paragraph (g) 

of AD 2008–17–15. 

(4) The revision required by paragraph (k) 

of AD 2011–18–03. 

(5) All requirements of AD 2013–15–17. 

(6) The revisions required by paragraphs 

(i)(1)(i) through (iii) of AD 2018–20–13. 

(7) All requirements of AD 2018–20–24. 

(k) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Seattle 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 paragraph (l) of this 

AD. Information may be emailed to: 9-ANMSeattle-ACO-AMOC-Requests@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. 

(3) An AMOC that provides an acceptable 

level of safety may be used for any repair, 

modification, or alteration required by this 

AD if it is approved by The Boeing Company 

Organization Designation Authorization 

(ODA) that has been authorized by the 

Manager, Seattle ACO Branch, FAA, to make 

those findings. To be approved, the repair 

method, modification deviation, or alteration 

deviation must meet the certification basis of 

the airplane, and the approval must 

specifically refer to this AD. 

(l) Related Information 

For more information about this AD, 

contact Christopher Baker, Aerospace 

Engineer, Propulsion Section, FAA, Seattle 

ACO Branch, 2200 South 216th St., Des 

Moines, WA 98198; phone and fax: 206–231– 

3552; email: Christopher.R.Baker@faa.gov. 

(m) 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 the AD specifies otherwise. 

(i) Boeing 737–600/700/700C/800/900/ 

900ER Special Compliance Items/ 

Airworthiness Limitations, D626A001–9–04, 

dated April 2019. 

(ii) Boeing 737–600/700/700C/800/900/ 

900ER Special Compliance Items/ 

Airworthiness Limitations, D626A001–9–04, 

dated November 2020. 

(3) For service information identified in 

this AD, contact Boeing Commercial 

Airplanes, Attention: Contractual & Data 

Services (C&DS), 2600 Westminster Blvd., 

MC 110–SK57, Seal Beach, CA 90740–5600; 

telephone 562–797–1717; internet https://

www.myboeingfleet.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 fedreg.legal@nara.gov, or go to: https:// 

www.archives.gov/federal-register/cfr/ibrlocations.html. 

Issued on May 21, 2021. 

Lance T. Gant, 

Director, Compliance & Airworthiness 

Division, Aircraft Certification Service. 

[FR Doc. 2021–12436 Filed 6–14–21; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2021–0314; Project 

Identifier MCAI–2020–00599–R; Amendment 

39–21592; AD 2021–12–05] 

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 EC155B1 

helicopters. This AD was prompted by 

a report of difficulties when jettisoning 

the co-pilot door during non-scheduled 

maintenance. This AD requires a 

functional check of the pilot and copilot door jettisoning system and 

corrective actions if necessary, as 

specified in a European 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 20, 

2021. 


khammond on DSKJM1Z7X2PROD with RULES
31610 Federal Register / Vol. 86, No. 113 / Tuesday, June 15, 2021 / Rules and Regulations 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of July 20, 2021. 

ADDRESSES: For material incorporated 

by reference (IBR) in this AD, contact 

the 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 

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 on the 

internet at https://www.regulations.gov 

by searching for and locating Docket No. 

FAA–2021–0314. 

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– 

0314; 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: 

Kathleen Arrigotti, Program Manager, 

Large Aircraft Section, International 

Validation Branch, Compliance & 

Airworthiness Division, FAA, 2200 

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

telephone and fax 206–231–3218; email 

kathleen.arrigotti@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Background 

The EASA (now European Union 

Aviation Safety Agency), which is the 

Technical Agent for the Member States 

of the European Union, has issued 

EASA AD 2015–0157, dated July 30, 

2015 (EASA AD 2015–0157) (also 

referred to as the Mandatory Continuing 

Airworthiness Information, or the 

MCAI), to correct an unsafe condition 

for Airbus Helicopters Model EC 155 B1 

helicopters, all serial numbers delivered 

after manufacturing before June 30, 

2015, and equipped with a pilot or copilot door jettisoning system in 

accordance with Airbus Helicopters 

Modification POST MOD 0752C05, 

except helicopters on which Aircraft 

Maintenance Manual (AMM) Task 52– 

11–00–712 was accomplished on both 

pilot and co-pilot doors since the last 

crew door installation. 

The FAA issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 by adding an AD that would 

apply to certain Airbus Helicopters 

Model EC155B1 helicopters. The NPRM 

published in the Federal Register on 

April 22, 2021 (86 FR 21240). The 

NPRM was prompted by a report of 

difficulties when jettisoning the co-pilot 

door during non-scheduled 

maintenance. The NPRM proposed to 

require a functional check of the pilot 

and co-pilot door jettisoning system and 

corrective actions if necessary, as 

specified in an EASA AD. 

The FAA is issuing this AD to address 

jamming of the affected door jettisoning 

mechanism, which could reduce the 

ability of the flightcrew to evacuate in 

the event of an emergency situation. See 

the MCAI for additional background 

information. 

Discussion of Final Airworthiness 

Directive 

Comments 

The FAA gave the public the 

opportunity to participate in developing 

this final rule. The FAA received no 

comments on the NPRM or on the 

determination of the cost to the public. 

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 NPRM for 

addressing the unsafe condition; and 

• Do not add any additional burden 

upon the public than was already 

proposed in the NPRM. 

Related Service Information Under 1 

CFR Part 51 

EASA AD 2015–0157 specifies 

procedures for doing a functional check 

of the pilot and co-pilot door jettisoning 

system and corrective actions. The 

corrective actions include greasing the 

tenons and restoring the jettison system. 

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. 

Costs of Compliance 

The FAA estimates that this AD 

affects 14 helicopters 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 

8 work-hours × $85 per hour = $680 .......................................................................................... $0 $680 $9,520 

The FAA estimates the following 

costs to do any necessary on-condition 

action 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 

this on-condition action: 

ESTIMATED COSTS OF ON-CONDITION ACTIONS

Labor cost Parts cost Cost per 

product 

1 work-hour × $85 per hour = $85 .......................................................................................................................... $0 $85 


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Federal Register / Vol. 86, No. 113 / Tuesday, June 15, 2021 / Rules and Regulations 31611 

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: 

2021–12–05 Airbus Helicopters: 

Amendment 39–21592; Docket No. 

FAA–2021–0314; Project Identifier 

MCAI–2020–00599–R. 

(a) Effective Date 

This airworthiness directive (AD) is 

effective July 20, 2021. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to Airbus Helicopters 

Model EC155B1 helicopters, certificated in 

any category, all serial numbers 

manufactured before June 30, 2015, and 

equipped with a pilot or co-pilot door 

jettisoning system in accordance with Airbus 

Helicopters modification POST MOD 

0752C05, except helicopters on which 

Aircraft Maintenance Manual (AMM) task 

52–11–00–712 was accomplished on both 

pilot and co-pilot doors since the last crew 

door installation. 

(d) Subject 

Joint Aircraft System Component (JASC) 

Code 5210, Passenger/Crew Doors. 

(e) Reason 

This AD was prompted by a report of 

difficulties when jettisoning the co-pilot door 

during non-scheduled maintenance. The 

FAA is issuing this AD to address jamming 

of the affected door jettisoning mechanism, 

which could reduce the ability of the 

flightcrew to evacuate in the event of an 

emergency situation. 

(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 European Aviation Safety 

Agency (now European Union Aviation 

Safety Agency) (EASA) AD 2015–0157, dated 

July 30, 2015 (EASA AD 2015–0157). 

(h) Exceptions to EASA AD 2015–0157 

(1) Where EASA AD 2015–0157 refers to its 

effective date, this AD requires using the 

effective date of this AD. 

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

2015–0157 does not apply to this AD. 

(3) Where EASA AD 2015–0157 refers to 

flight hours (FH), this AD requires using 

hours time-in-service. 

(4) Where paragraph (2) of EASA AD 2015– 

0157 provides an option to contact Airbus 

Helicopters for approved instructions and 

accomplish those instructions, for this AD, 

the option is to repair the jettison system in 

accordance with FAA-approved procedures. 

(5) Where the service information 

referenced in EASA AD 2015–0157 specifies 

to ‘‘speak to Airbus Helicopters,’’ this AD 

requires repairing the jettison system in 

accordance with FAA-approved procedures. 

(6) Where the service information 

referenced in EASA AD 2015–0157 specifies 

to discard certain parts, this AD requires 

removing the parts from service instead. 

(i) 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 (j) 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. 

(j) Related Information 

For more information about this AD, 

contact Kathleen Arrigotti, Program Manager, 

Large Aircraft Section, International 

Validation Branch, Compliance & 

Airworthiness Division, FAA, 2200 South 

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

and fax 206–231–3218; email 

kathleen.arrigotti@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 Aviation Safety Agency 

(EASA) AD 2015–0157, dated July 30, 2015. 

(ii) [Reserved] 

(3) For EASA AD 2015–0157, contact the 

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 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. 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–2021–0314. 

(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 27, 2021. 

Lance T. Gant, 

Director, Compliance & Airworthiness 

Division, Aircraft Certification Service. 

[FR Doc. 2021–12482 Filed 6–14–21; 8:45 am] 

BILLING CODE 4910–13–P 


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