This section of the FEDERAL REGISTER

contains regulatory documents having general

applicability and legal effect, most of which

are keyed to and codified in the Code of

Federal Regulations, which is published under

50 titles pursuant to 44 U.S.C. 1510.

The Code of Federal Regulations is sold by

the Superintendent of Documents.

Rules and Regulations Federal Register

10057 

Vol. 87, No. 36 

Wednesday, February 23, 2022 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2021–1166; Project 

Identifier MCAI–2021–00952–R; Amendment 

39–21953; AD 2022–05–02] 

RIN 2120–AA64 

Airworthiness Directives; Airbus 

Helicopters (Type Certificate 

Previously Held by Eurocopter France) 

Helicopters 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: The FAA is superseding 

Airworthiness Directive (AD) 2021–11– 

25, which applied to certain Airbus 

Helicopters (type certificate previously 

held by Eurocopter France) Model 

AS350B3 and EC130T2 helicopters. AD 

2021–11–25 required revising the 

existing rotorcraft flight manual (RFM) 

for your helicopter by inserting a new 

procedure (temporary). Since the FAA 

issued AD 2021–11–25, the 

manufacturer identified an additional 

affected full authority digital engine 

control (FADEC) part number and 

developed an optional modification for 

the affected FADECs. This AD requires 

revising the existing RFM for your 

helicopter by inserting a new procedure 

(temporary). This AD also requires, for 

helicopter on which an optional 

terminating action (installation of 

serviceable FADECs) was done, 

removing the applicable temporary 

procedure from the existing RFM for 

your helicopter. In addition, this AD 

also adds helicopters to the 

applicability. Furthermore, this AD 

prohibits the installation of an affected 

FADEC. The FAA is issuing this AD to 

address the unsafe condition on these 

products. 

DATES: This AD is effective March 30, 

2022. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in this AD 

as of July 29, 2021 (86 FR 33097, June 

24, 2021). 

ADDRESSES: For Airbus Helicopters 

service information identified in this 

final rule, contact Airbus Helicopters, 

2701 N Forum Drive, Grand Prairie, TX 

75052; telephone (972) 641–0000 or 

(800) 232–0323; fax (972) 641–3775; or 

at https://www.airbus.com/helicopters/

services/technical-support.html. For 

Safran Turbomeca service information 

identified in this NPRM contact Safran 

Helicopter Engines, S.A., 64511 Bordes, 

France; phone: +33 (0) 5 59 74 45 11. 

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. Service 

information that is incorporated by 

reference is also available at https://

www.regulations.gov by searching for 

and locating Docket No. FAA–2021– 

1166. 

Examining the AD Docket 

You may examine the AD docket at 

https://www.regulations.gov by 

searching for and locating Docket No. 

FAA–2021–1166; or in person at Docket 

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

Monday through Friday, except Federal 

holidays. The AD docket contains this 

final rule, the European Union Aviation 

Safety Agency (EASA) AD, any 

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: 

Andrea Jimenez, Aerospace Engineer, 

COS Program Management Section, 

Operational Safety Branch, Compliance 

& Airworthiness Division, FAA, 1600 

Stewart Ave., Suite 410, Westbury, NY 

11590; telephone (516) 228–7330; email 

andrea.jimenez@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Background 

The FAA issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to supersede AD 2021–11–25, 

Amendment 39–21587 (86 FR 33097, 

June 24, 2021), (AD 2021–11–25). AD 

2021–11–25 applied to Airbus 

Helicopters (type certificate previously 

held by Eurocopter France) Model 

AS350B3 and EC130T2 helicopters with 

an ARRIEL 2D engine and THALES 

FADEC part number (P/N) C13165DA00 

without amendment A or THALES 

FADEC P/N C13165FA00 without 

amendment B, installed. The NPRM 

published in the Federal Register on 

December 28, 2021 (86 FR 73703). In the 

NPRM, the FAA proposed to require 

revising the existing RFM for your 

helicopter by inserting a new procedure 

(temporary). The NPRM also proposed 

to require, for helicopters on which an 

optional terminating action (installation 

of serviceable FADECs) is done, 

removing the applicable temporary 

procedure from the existing RFM for 

your helicopter. In addition, the NPRM 

also proposed to add helicopters to the 

applicability. Furthermore, the NPRM 

proposed to prohibit the installation of 

an affected FADEC. 

AD 2021–11–25 was prompted by 

EASA AD 2013–0287, dated December 

5, 2013 (EASA AD 2013–0287), issued 

by EASA, which is the Technical Agent 

for the Member States of the European 

Union, to correct an unsafe condition 

for Eurocopter (formerly Eurocopter 

France, Aerospatiale) Model AS 350 B3 

and EC 130 T2 helicopters with an 

ARRIEL 2D engine and THALES FADEC 

P/N C13165DA00 or P/N C13165FA00 

installed. EASA advised that there was 

a report of an in-flight event where the 

pilot noticed that the temporary amber 

governor (GOV) light had illuminated, 

followed by the failure of the vehicle 

engine monitoring display (VEMD) 

screens, and no availability of the 

automatic or auxiliary engine back-up 

control ancillary unit (EBCAU). 

Subsequent investigation identified an 

internal failure of the engine digital 

electronic control unit (DECU), which 

led to loss of fuel flow regulation (frozen 

fuel metering unit). This failure was not 

indicated to the pilot by a red GOV 

warning light as expected, but with 

amber GOV indication and loss of 

VEMD display instead. EASA also 

advised that if this fuel metering unit is 

frozen in the open position, it may lead 

to a rotor overspeed, and if it is frozen 

in the closed position, it may lead to 

unavailability of engine power. EASA 

stated that this condition, if not 

addressed, could result in the pilot 


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identifying the type of failure condition 

incorrectly, possibly resulting in an 

improper response. 

Since the FAA issued AD 2021–11– 

25, EASA issued AD 2021–0195, dated 

August 20, 2021 (EASA AD 2021–0195), 

which supersedes EASA AD 2013–0287. 

EASA advises that after EASA AD 

2013–0287 was issued, Airbus 

Helicopters revised Alert Service 

Bulletin No. AS350–01.00.67, Revision 

2, dated February 17, 2014; and Alert 

Service Bulletin No. EC130–04A004, 

Revision 2, dated February 17, 2014; to 

include an additional affected part 

number as part of the same rectification 

campaign. Additionally, EASA advises 

that in parallel, SAFRAN (formerly 

Turbome ́ca) developed a modification of 

the affected part, which mitigates the 

risk of rotor speed fluctuations, loss of 

power or uncommanded in-flight 

shutdown, and issued Service Bulletin 

292 73 2852 providing FADEC 

replacement instructions. Consequently, 

Airbus Helicopters issued the applicable 

ASBs, providing instructions to remove 

the temporary procedure from the RFM 

Emergency Procedures section for 

helicopters with a modified FADEC. 

Accordingly, EASA AD 2021–0195 

retains the requirements of EASA AD 

2013–0287 and requires removing the 

temporary revision from the Emergency 

Procedures section of the RFM for 

helicopters with a modified FADEC 

installed. EASA AD 2021–0195 also 

prohibits the installation of an affected 

part after installation of a modified 

FADEC. Furthermore, EASA AD 2021– 

0195 specifies to ‘‘inform all flight 

crews’’ of revisions to the RFM, and 

thereafter to ‘‘operate the helicopter 

accordingly.’’ 

Discussion of Final Airworthiness 

Directive 

Comments 

The FAA received no comments on 

the NPRM or on the determination of 

the costs. 

Conclusion 

These helicopters have been approved 

by EASA and are approved for operation 

in the United States. Pursuant to the 

FAA’s bilateral agreement with the 

European Union, EASA has notified the 

FAA about the unsafe condition 

described in its AD. The FAA reviewed 

the relevant data and determined that 

air safety requires adopting this AD as 

proposed. Accordingly, the FAA is 

issuing this AD to address the unsafe 

condition on these helicopters. Except 

for minor editorial changes, this AD is 

adopted as proposed in the NPRM. 

Related Service Information Under 1 

CFR Part 51 

The FAA reviewed Airbus Helicopters 

Alert Service Bulletin No. AS350– 

01.00.67, Revision 2, dated February 17, 

2014; and Alert Service Bulletin No. 

EC130–04A004, Revision 2, dated 

February 17, 2014; which the Director of 

the Federal Register approved for 

incorporation by reference as of July 29, 

2021. 

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. 

Other Related Service Information 

The FAA also reviewed Safran 

Turbomeca Mandatory Service Bulletin 

No. 292 73 2852, Revision C, dated June 

6, 2016. This service information 

specifies replacing certain FADEC D 

EECUs with certain amended FADEC D 

EECUs. 

Differences Between This AD and the 

EASA AD 

EASA AD 2021–0195 requires 

operators to ‘‘inform all flight crews’’ of 

revisions to the RFM, and thereafter to 

‘‘operate the helicopter accordingly.’’ 

However, this AD does not specifically 

require those actions. 

FAA regulations mandate compliance 

with only the operating limitations 

section of the flight manual. The flight 

manual changes required by this AD 

apply to the emergency procedures 

section of the existing RFM for your 

helicopter. Furthermore, compliance 

with such requirements in an AD is 

impracticable to demonstrate or track on 

an ongoing basis; therefore, a 

requirement to operate the aircraft in 

such a manner is unenforceable. 

Nonetheless, the FAA recommends that 

flight crews of the helicopters listed in 

the applicability operate in accordance 

with the revised emergency procedures 

specified in this AD. 

Costs of Compliance 

The FAA estimates that this AD 

affects up to 628 helicopters of U.S. 

Registry. Labor rates are estimated at 

$85 per work-hour. Based on these 

numbers, the FAA estimates the 

following costs to comply with this AD. 

Revising the existing RFM for your 

helicopter takes about 0.25 work-hour 

for an estimated cost of $21 per 

helicopter and up to $13,188 for the 

U.S. fleet. Accomplishing the optional 

terminating action, if done, takes about 

1 work-hour, with a parts costs of 

$5,000, for an estimated cost of $5,085 

per helicopter. 

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: 


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Federal Register / Vol. 87, No. 36 / Wednesday, February 23, 2022 / Rules and Regulations 10059 

■ a. Removing Airworthiness Directive 

2021–11–25, Amendment 39–21587 (86 

FR 33097, June 24, 2021); and 

■ b. Adding the following new 

airworthiness directive: 

2022–05–02 Airbus Helicopters (Type 

Certificate Previously Held by 

Eurocopter France): Amendment 39– 

21953; Docket No. FAA–2021–1166; 

Project Identifier MCAI–2021–00952–R. 

(a) Effective Date 

This airworthiness directive (AD) is 

effective March 30, 2022. 

(b) Affected ADs 

This AD replaces AD 2021–11–25, 

Amendment 39–21587 (86 FR 33097, June 

24, 2021) (AD 2021–11–25). 

(c) Applicability 

This AD applies to Airbus Helicopters 

(type certificate previously held by 

Eurocopter France) Model AS350B3 and 

EC130T2 helicopters, certificated in any 

category, with an ARRIEL 2D engine and 

with THALES full authority digital engine 

control (FADEC) part number (P/N) 

C13165DA00 without amendment A, P/N 

C13165DA00PC00 without amendment A, or 

P/N C13165FA00 without amendment B, that 

has a serial number below 1736, installed. 

Note 1 to paragraph (c): Helicopters with 

a Model AS350B3e designation are Model 

AS350B3 helicopters. 

(d) Subject 

Joint Aircraft Service Component (JASC) 

Code: 7321, Engine Fuel Control/Turbine 

Engines. 

(e) Unsafe Condition 

This AD was prompted by a report of 

failure of an engine digital electronic control 

unit. The FAA is issuing this AD to prevent 

incorrect indicator illumination, display 

failure, and loss of fuel flow regulation 

(frozen fuel metering unit). The unsafe 

condition, if not addressed, could result in 

misleading information to the pilot, rotor 

overspeed or unavailability of engine power, 

and subsequent loss of control of the 

helicopter. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Retained Revision to the Existing 

Rotorcraft Flight Manual (RFM) for Your 

Helicopter and Optional Terminating Action 

for Certain Helicopters With New Optional 

Terminating Action 

For helicopters with FADEC P/N 

C13165DA00 without amendment A or P/N 

C13165FA00 without amendment B 

installed: 

(1) Within 25 hours time-in-service after 

July 29, 2021 (the effective date of AD 2021– 

11–25), revise the Emergency Procedures of 

the existing RFM for your helicopter by 

inserting Appendix 4. of Airbus Helicopters 

Alert Service Bulletin (ASB) No. AS350– 

01.00.67 or ASB No. EC130–04A004, each 

Revision 2 and dated February 17, 2014 (ASB 

AS350–01.00.67 or ASB EC130–04A004), as 

applicable to your helicopter model. 

Inserting a different document with 

information identical to that in Appendix 4. 

of ASB AS350–01.00.67 or ASB EC130– 

04A004, as applicable to your helicopter 

model, is acceptable for compliance with the 

requirement of this paragraph. 

(2) As an optional terminating action for 

the requirement of paragraph (g)(1) of this 

AD, install amendment A on FADEC P/N 

C13165DA00 or amendment B on FADEC 

P/N C13165FA00. 

(3) As an optional terminating action for 

the requirement of paragraph (g)(1) of this 

AD, install a FADEC unit having P/N 

C13165DA00 with amendment A, P/N 

C13165DA00PC00 with amendment A, or 

;P/N C13165FA00 with amendment B; or 

install a FADEC unit other than a FADEC 

unit having P/N C13165DA00, P/N 

C13165DA00PC00, or P/N C13165FA00, that 

has a serial number below 1736. 

(h) New Requirement: Revision to the 

Existing RFM for Your Helicopter and 

Optional Terminating Action for Certain 

Other Helicopters 

For helicopters that have FADEC P/N 

C13165DA00PC00 without amendment A 

installed: 

(1) Within 25 hours time-in-service after 

the effective date of this AD, revise the 

existing RFM for your helicopter by inserting 

Appendix 4. of ASB AS350–01.00.67 or ASB 

EC130–04A004, as applicable to your 

helicopter model. Inserting a different 

document with information identical to that 

in Appendix 4. of ASB AS350–01.00.67 or 

ASB EC130–04A004, as applicable to your 

helicopter model, is acceptable for 

compliance with the requirement of this 

paragraph. 

(2) As an optional terminating action for 

the requirement of paragraph (h)(1) of this 

AD, install amendment A on FADEC P/N 

C13165DA00PC00. 

(3) As an optional terminating action for 

the requirement of paragraph (h)(1) of this 

AD, install a FADEC unit having P/N 

C13165DA00 with amendment A, P/N 

C13165DA00PC00 with amendment A, or 

;P/N C13165FA00 with amendment B; or 

install a FADEC unit other than a FADEC 

unit having P/N C13165DA00, P/N 

C13165DA00PC00, or P/N C13165FA00, that 

has a serial number below 1736. 

(i) New Requirement: Removal of Temporary 

Revision From the Existing RFM for Your 

Helicopter 

(1) For helicopters that accomplish the 

optional terminating action specified in 

paragraph (g)(2) or (3) of this AD: 

Concurrently with the installation, before 

further flight, remove the temporary revision 

to the existing RFM for your helicopter that 

was inserted in accordance with the 

requirement of paragraph (g)(1) of this AD. 

(2) For helicopters that accomplish the 

optional terminating action specified in 

paragraph (h)(2) or (3) of this AD: 

Concurrently with the installation, before 

further flight, remove the temporary revision 

to the existing RFM for your helicopter that 

was inserted in accordance with the 

requirement of paragraph (h)(1) of this AD. 

(j) Parts Installation Prohibition 

As of the effective date of this AD, no 

person may install on any helicopter a 

FADEC identified in paragraph (c) of this AD 

(affected FADEC part). 

Note 2 to paragraph (j): Removal of an 

affected FADEC part from a helicopter and 

reinstallation of that same affected FADEC 

part on the same helicopter during the same 

maintenance visit is not considered ‘‘install’’ 

as specified in paragraph (j) of this AD. 

(k) Special Flight Permits 

Special flight permits may be issued to 

operate the helicopter to a location where the 

actions specified in this AD can be 

performed, provided no passengers are 

onboard. 

(l) 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 (m)(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. 

(m) Related Information 

(1) For more information about this AD, 

contact Andrea Jimenez, Aerospace Engineer, 

COS Program Management Section, 

Operational Safety Branch, Compliance & 

Airworthiness Division, FAA, 1600 Stewart 

Ave., Suite 410, Westbury, NY 11590; 

telephone (516) 228–7330; email 

andrea.jimenez@faa.gov. 

(2) The subject of this AD is addressed in 

European Union Aviation Safety Agency 

(EASA) AD 2021–0195, dated August 20, 

2021. You may view the EASA AD on the 

internet at https://www.regulations.gov in 

Docket No. FAA–2021–1166. 

(n) 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. 

(3) The following service information was 

approved for IBR on July 29, 2021 (86 FR 

33097, June 24, 2021). 

(i) Airbus Helicopters Alert Service 

Bulletin No. AS350–01.00.67, Revision 2, 

dated February 17, 2014. 

(ii) Airbus Helicopters Alert Service 

Bulletin No. EC130–04A004, Revision 2, 

dated February 17, 2014. 

(4) For Airbus Helicopters service 

information identified in this AD, contact 


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

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

ibr-locations.html. 

Issued on February 16, 2022. 

Lance T. Gant, 

Director, Compliance & Airworthiness 

Division, Aircraft Certification Service. 

[FR Doc. 2022–03761 Filed 2–22–22; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2021–0457; Project 

Identifier AD–2020–01461–T; Amendment 

39–21911; AD 2022–02–14] 

RIN 2120–AA64 

Airworthiness Directives; The Boeing 

Company Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: The FAA is adopting a new 

airworthiness directive (AD) for certain 

The Boeing Company Model 787–8, 

787–9, and 787–10 airplanes. This AD 

was prompted by a report that during a 

fleet sampling inspection, cracks were 

found on the inner cylinder pivot pins 

of the left and right main landing gear 

(MLG) on one of the airplanes. This AD 

requires repetitive lubrications of the 

left and right MLG truck beams and 

inner cylinder pivot joints; a review of 

the maintenance program 

documentation to verify that certain 

lubrication tasks are incorporated; 

repetitive inspections of the MLG inner 

cylinder pivot pins and inner cylinder 

bushings of the MLG truck beams and 

inner cylinder joints to detect friction, 

heat damage, excessive wear, cracking, 

and smearing of bushing material; and 

applicable on-condition actions. The 

FAA is issuing this AD to address the 

unsafe condition on these products. 

DATES: This AD is effective March 30, 

2022. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in this AD 

as of March 30, 2022. 

ADDRESSES: For service information 

identified in this final rule, 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. 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 at https://

www.regulations.gov by searching for 

and locating Docket No. FAA–2021– 

0457. 

Examining the AD Docket 

You may examine the AD docket at 

https://www.regulations.gov by 

searching for and locating Docket No. 

FAA–2021–0457; 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: 

Allen Rauschendorfer, Senior Aerospace 

Engineer, Airframe Section, FAA, 

Seattle ACO Branch, 2200 South 216th 

St., Des Moines, WA 98198; phone and 

fax: 206–231–3528; email: 

allen.rauschendorfer@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Background 

The FAA issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 by adding an AD that would 

apply to certain The Boeing Company 

Model 787–8, 787–9, and 787–10 

airplanes. The NPRM published in the 

Federal Register on June 30, 2021 (86 

FR 34656). The NPRM was prompted by 

a report that during a fleet sampling 

inspection, cracks were found on the 

inner cylinder pivot pins of the left and 

right MLG on one of the airplanes. In 

the NPRM, the FAA proposed to require 

repetitive lubrications of the left and 

right MLG truck beams and inner 

cylinder pivot joints; a review of the 

maintenance program documentation to 

verify that certain lubrication tasks are 

incorporated; repetitive inspections of 

the MLG inner cylinder pivot pins and 

inner cylinder bushings of the MLG 

truck beams and inner cylinder joints to 

detect friction, heat damage, excessive 

wear, cracking, and smearing of bushing 

material; and applicable on-condition 

actions. The FAA is issuing this AD to 

address any heat damage and cracking 

to the MLG inner cylinder pivot pin, 

which could result in a fractured pivot 

pin and lead to loss of all or part of the 

pivot pin assembly, and subsequent 

collapse of the MLG and reduced 

controllability of the airplane during 

takeoff and landing. 

Discussion of Final Airworthiness 

Directive 

Comments 

The FAA received comments from 

The Air Line Pilots Association, 

International (ALPA) and Boeing. ALPA 

and Boeing supported the NPRM 

without change. 

The FAA received additional 

comments from four commenters, 

including American Airlines (AAL), 

Japan Airlines (JAL), United Airlines 

(UAL), and Virgin Atlantic Airways 

(VAA). The following presents the 

comments received on the NPRM and 

the FAA’s response to each comment. 

Request To Exclude Certain Airplanes 

From the Proposed AD 

UAL requested that the FAA revise 

the applicability of the proposed AD to 

exclude Model 787–9 and 787–10 

airplanes on which the left and right 

MLG truck beams and inner cylinder 

pivot joints have been repetitively 

lubricated with MIL–PRF–32014 grease 

from the date of airplane delivery. UAL 

stated that the compliance actions 

specified in Boeing Alert Service 

Bulletin B787–81205–SB320045–00, 

Issue 001, dated November 9, 2020, do 

not give any consideration to operators 

who have met the requirements of CMR 

item number 32–CMR–01 of Section G, 

‘‘Certification Maintenance Requirement 

Task,’’ of Boeing 787 Certification 

Maintenance Requirements (CMRs), 

D011Z009–03–03, dated June 2020 

(specified in paragraph (i) of the 

proposed AD for the optional 

maintenance/inspection program 

revision), since airplane delivery, as 

specified in Table 1 in the Work 

Instructions of the service bulletin. UAL 

also commented that Boeing Alert 

Service Bulletin B787–81205– 

SB320045–00, Issue 001, dated 

November 9, 2020, provides an option 

to terminate the repetitive inspections if 

copper-nickel-tin inner cylinder 

bushings are installed, and current or 

prior accomplishment of the increased 

lubrication interval with MIL–PRF– 


khammond on DSKJM1Z7X2PROD with RULES