19378 Federal Register / Vol. 87, No. 64 / Monday, April 4, 2022 / Rules and Regulations 

FAA–2021–1176; Project Identifier 

MCAI–2021–00755–R. 

(a) Effective Date 

This airworthiness directive (AD) is 

effective May 9, 2022. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to Airbus Helicopters 

Model SA330J helicopters, certificated in any 

category, as identified in European Union 

Aviation Safety Agency (EASA) AD 2021– 

0152R1, dated July 20, 2021 (EASA AD 

2021–0152R1). 

(d) Subject 

Joint Aircraft Service Component (JASC) 

Code: 6300, Main Rotor Drive System. 

(e) Unsafe Condition 

This AD was prompted by a review of 

Airbus Helicopters Model EC225LP 

helicopter data that revealed potential 

tightening torque loss of the attachment 

screws of the upper deck fittings of the three 

main gearbox (MGB) suspension bars. Due to 

design similarities, the MGB right-hand (RH) 

rear fittings and MGB RH rear fitting 

attachment screws on Model SA330J 

helicopters could also be affected. Additional 

analysis confirmed that the service life limit 

(life limit) (SLL) for the affected MGB RH rear 

fittings needs to be reduced for helicopters 

on which these affected parts were operated 

concurrently with metallic main rotor blades 

installed. The FAA is issuing this AD to 

address tightening torque loss of the 

attachment screws of the upper deck fittings 

of the three MGB suspension bars. The 

unsafe condition, if not addressed, could 

result in structural failure of the MGB RH 

rear fittings and MGB RH rear fitting 

attachment screws, resulting in detachment 

of the MGB suspension bars and consequent 

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, EASA AD 2021–0152R1. 

(h) Exceptions to EASA AD 2021–0152R1 

(1) Where EASA AD 2021–0152R1 requires 

compliance in terms of flight hours, this AD 

requires using hours time-in-service. 

(2) Where EASA AD 2021–0152R1 refers to 

July 9, 2021 (the effective date of EASA AD 

2021–0152R1, dated June 25, 2021), this AD 

requires using the effective date of this AD. 

(3) Where the service information 

referenced in EASA AD 2021–0152R1 

specifies discarding parts, this AD requires 

removing those parts from service. 

(4) Although the service information 

referenced in EASA AD 2021–0152R1 

specifies that ‘‘The work must be performed 

on the helicopter by the operator.’’ this AD 

does not require that the operator perform the 

work. 

(5) This AD does not mandate compliance 

with the ‘‘Remarks’’ section of EASA AD 

2021–0152R1. 

(6) The preliminary steps specified in 

paragraph 3.B.1. of the service information 

referenced in EASA AD 2021–0152R1 are not 

required for compliance with this AD. 

(7) Although the service information 

referenced in EASA AD 2021–0152R1 

specifies contacting Airbus Helicopters if the 

time since new (TSN) is unknown at the 

retrofit date, this AD requires determining 

the damage value and the SLL of each 

affected part but does not require contacting 

Airbus Helicopters if the TSN is unknown at 

the retrofit date. 

(i) No Reporting Requirement 

Although the service information 

referenced in EASA AD 2021–0152R1 

specifies to submit certain information to the 

manufacturer, this AD does not include that 

requirement. 

(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 Hal Jensen, Aerospace Engineer, 

Operational Safety Branch, FAA, 950 

L’Enfant Plaza SW, Washington, DC 20024; 

telephone: (202) 267–9167; email: 

hal.jensen@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 this AD specifies otherwise. 

(i) European Union Aviation Safety Agency 

(EASA) AD 2021–0152R1, dated July 20, 

2021. 

(ii) [Reserved]. 

(3) For EASA AD 2021–0152R1, 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 the 

EASA material 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 

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

for and locating Docket No. FAA–2021–1176. 

(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 

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

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

Issued on March 10, 2022. 

Lance T. Gant, 

Director, Compliance & Airworthiness 

Division, Aircraft Certification Service. 

[FR Doc. 2022–06940 Filed 4–1–22; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2021–0999; Project 

Identifier MCAI–2021–00036–A; Amendment 

39–21991; AD 2022–07–04] 

RIN 2120–AA64 

Airworthiness Directives; Pilatus 

Aircraft Ltd. Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: The FAA is adopting a new 

airworthiness directive (AD) for certain 

Pilatus Aircraft Ltd. (Pilatus) Model PC– 

12/47E airplanes. This AD was 

prompted by mandatory continuing 

airworthiness information (MCAI) 

originated by an aviation authority of 

another country to identify and correct 

an unsafe condition on an aviation 

product. The MCAI identifies the unsafe 

condition as inward vent valves 

installed during production without 

chromate conversion coating on the 

bonding surface. This AD requires 

modifying the inward vent valves and 

prohibits installing unmodified inward 

vent valves. The FAA is issuing this AD 

to address the unsafe condition on these 

products. 

DATES: This AD is effective May 9, 2022. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in this AD 

as of May 9, 2022. 

ADDRESSES: For service information 

identified in this final rule, contact 

Pilatus Aircraft Ltd., CH–6371, Stans, 

Switzerland; phone: +41 848 247 365; 

email: techsupport.ch@pilatusaircraft.com; website: https://

www.pilatus-aircraft.com/. You may 


khammond on DSKJM1Z7X2PROD with RULES
Federal Register / Vol. 87, No. 64 / Monday, April 4, 2022 / Rules and Regulations 19379 

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 (817) 222–5110. It is also 

available at https://www.regulations.gov 

by searching for and locating Docket No. 

FAA–2021–0999. 

Examining the AD Docket 

You may examine the AD docket at 

https://www.regulations.gov by 

searching for and locating Docket No. 

FAA–2021–0999; 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 MCAI, 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: 

Doug Rudolph, Aviation Safety 

Engineer, FAA, General Aviation & 

Rotorcraft Section, International 

Validation Branch, 901 Locust, Room 

301, Kansas City, MO 64106; phone: 

(816) 329–4059; email: doug.rudolph@

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 serial-numbered Pilatus 

Model PC–12/47E airplanes. The NPRM 

published in the Federal Register on 

November 12, 2021 (86 FR 62746). The 

NPRM was prompted by MCAI from the 

European Union Aviation Safety Agency 

(EASA), which is the Technical Agent 

for the Member States of the European 

Union. EASA issued AD 2021–0010, 

dated January 11, 2021 (referred to after 

this as ‘‘the MCAI’’), to correct an unsafe 

condition for Pilatus Model PC–12/47E 

airplanes with serial number 1720 and 

serial number 2001 and higher. The 

MCAI states: 

An occurrence was reported where, on the 

production line, a batch of inward vent 

valves without a chromate conversion 

coating on the bonding surface were installed 

on some PC–12/47E aeroplanes. Such inward 

vent valves are not in compliance with the 

latest approved design data. 

This condition, if not corrected, could lead 

to corrosion, consequent degradation of the 

electrical bonding to Rib 16, and in case of 

lightning strike, to arcing between the 

ungrounded equipment and the primary 

structure, possibly resulting in a fire and 

reduced control of the aeroplane. 

To address this potential unsafe condition, 

Pilatus issued the SB [Service Bulletin] to 

provide modification instructions. 

For the reason described above, this 

[EASA] AD requires modification of each 

affected part, as defined in this AD. This 

[EASA] AD also prohibits (re-) installation of 

affected parts. 

You may examine the MCAI in the 

AD docket at https://

www.regulations.gov by searching for 

and locating Docket No. FAA–2021– 

0999. 

In the NPRM, the FAA proposed to 

require modifying the inward vent 

valves and proposed to prohibit 

installing unmodified inward vent 

valves. The FAA is issuing this AD to 

address the unsafe condition on these 

products. 

Discussion of Final Airworthiness 

Directive 

Comments 

The FAA received comments from 

Pilatus and PlaneSense Inc. 

(PlaneSense). The following presents 

the comments received on the NPRM 

and the FAA’s response to each 

comment. 

Request To Correct Service Bulletin 

References 

Pilatus and PlaneSense requested that 

the FAA correct an error in the service 

bulletin (SB) references in paragraphs 

(g)(1) and (2) of the proposed AD. 

Pilatus stated these paragraphs read 

‘‘Pilatus SB 20–015’’ when they should 

read ‘‘Pilatus SB 28–015.’’ 

The FAA agrees and has corrected the 

service bulletin references. 

Request To Revise the Definition of 

Group 2 Airplanes 

Pilatus requested the FAA revise the 

definition of Group 2 airplanes in 

paragraph (g)(2) of the proposed AD 

from ‘‘Airplanes without an inward vent 

valve P/N 963.04.26.520 installed with 

a serial number listed in section 1.C(1) 

of Pilatus SB 20–015’’ to ‘‘Airplanes 

with an inward vent valve P/N 

963.04.26.520 installed with a serial 

number not listed in section 1.C(1) of 

the Pilatus SB 28–015.’’ Pilatus stated 

the proposed definition is difficult to 

read and could be misinterpreted by an 

operator. 

The FAA disagrees. The language 

requested by Pilatus would change the 

scope of the prohibition installation in 

paragraph (i) of the proposed AD, such 

that it only applies to airplanes with 

inward vent valve P/N 963.04.26.520 

installed. The FAA intended the 

prohibition installation to apply to all 

airplanes that are not Group 1 airplanes, 

even those with a different inward vent 

valve P/N (such as valves manufactured 

by the holder of a parts manufacturer 

approval or if there is a part number 

change to the vent in the future). The 

FAA did not change the proposed AD as 

a result of this comment. 

PlaneSense requested the FAA limit 

the applicability in paragraph (c) of the 

proposed AD to those airplanes defined 

as Group 1 in the proposed AD, so that 

it matches the effectivity of Pilatus 

Service Bulletin 28–015. 

The FAA disagrees. Although the 

applicability of the proposed AD is 

broader than the Pilatus SB, it proposed 

to require that only Group 1 airplanes 

have the inward vent valves modified in 

accordance with the Pilatus SB. The 

FAA proposed a broader applicability to 

prohibit installation of an affected 

inward vent valve on all airplanes that 

are not Group 1 airplanes. The FAA did 

not change the applicability of the 

proposed AD as a result of this 

comment. 

Conclusion 

This product has been approved by 

the aviation authority of another 

country and is approved for operation in 

the United States. Pursuant to the FAA’s 

bilateral agreement with this State of 

Design Authority, it has notified the 

FAA of the unsafe condition described 

in the MCAI and service information 

referenced above. The FAA reviewed 

the relevant data, considered the 

comments received, 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 products. Except for 

the changes described previously, this 

AD is adopted as proposed in the 

NPRM. None of the changes will 

increase the economic burden on any 

operator. 

Related Service Information Under 1 

CFR Part 51 

The FAA reviewed Pilatus Service 

Bulletin No. 28–015, dated October 12, 

2020, which contains information for 

identifying affected inward vent valves, 

removing the affected inward vent 

valve, and installing a modified inward 

vent valve. 

The FAA also reviewed Pall 

Corporation Service Bulletin SB9337– 

01–29–01, Issue 1, dated September 22, 

2020, which contains instructions for 

modifying the inward vent valve by 

applying corrosion protective chromate 

conversation coating. 

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. 


khammond on DSKJM1Z7X2PROD with RULES
19380 Federal Register / Vol. 87, No. 64 / Monday, April 4, 2022 / Rules and Regulations 

Costs of Compliance 

The FAA estimates that this AD will 

affect 24 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 

airplane 

Cost on U.S. 

operators 

Modification per airplane if both sides affected.3 work-hours × $85 per hour = $255 ............. $50 $305 $7,320 

The FAA has included all known 

costs in its cost estimate. According to 

the manufacturer, however, some of the 

costs of this AD may be covered under 

warranty, thereby reducing the cost 

impact on affected operators. 

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 this AD: 

(1) Is not a ‘‘significant regulatory 

action’’ under Executive Order 12866, 

(2) Will not affect intrastate aviation 

in Alaska, and 

(3) Will not have a significant 

economic impact, positive or negative, 

on a substantial number of small entities 

under the criteria of the Regulatory 

Flexibility Act. 

List of Subjects in 14 CFR Part 39 

Air transportation, Aircraft, Aviation 

safety, Incorporation by reference, 

Safety. 

The Amendment 

Accordingly, under the authority 

delegated to me by the Administrator, 

the FAA amends 14 CFR part 39 as 

follows: 

PART 39—AIRWORTHINESS 

DIRECTIVES 

■ 1. The authority citation for part 39 

continues to read as follows: 

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

§ 39.13 [Amended] 

■ 2. The FAA amends § 39.13 by adding 

the following new airworthiness 

directive: 

2022–07–04 Pilatus Aircraft Ltd.: 

Amendment 39–21991; Docket No. 

FAA–2021–0999; Project Identifier 

MCAI–2021–00036–A. 

(a) Effective Date 

This airworthiness directive (AD) is 

effective May 9, 2022. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to Pilatus Aircraft Ltd. 

Model PC–12/47E airplanes, serial number 

(S/N) 1720 and S/N 2001 and larger, 

certificated in any category. 

(d) Subject 

Joint Aircraft System Component (JASC) 

Code 2800, Aircraft Fuel System. 

(e) Unsafe Condition 

This AD was prompted by mandatory 

continuing airworthiness information (MCAI) 

originated by an aviation authority of another 

country to identify and correct an unsafe 

condition on an aviation product. The MCAI 

identifies the unsafe condition as inward 

vent valves installed during production 

without chromate conversion coating on the 

bonding surface. The FAA is issuing this AD 

to prevent corrosion and degradation of the 

electrical bonding to Rib 16. This condition, 

if not addressed, could lead to arcing 

between the ungrounded equipment and the 

primary structure in the event of a lightning 

strike, resulting in a fire and reduced 

airplane control. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Definitions 

(1) Group 1 airplanes: Airplanes with an 

inward vent valve part number (P/N) 

963.04.26.520 installed with a serial number 

listed in section 1.C(1) of Pilatus Service 

Bulletin No. 28–015, dated October 12, 2020 

(Pilatus SB 28–015). 

(2) Group 2 airplanes: Airplanes without 

an inward vent valve P/N 963.04.26.520 

installed with a serial number listed in 

section 1.C(1) of Pilatus SB 28–015. 

(h) Modification of Inward Vent Valves 

For Group 1 airplanes, within 1,200 hours 

time-in-service after the effective date of this 

AD or within 9 months after the effective 

date of this AD, whichever occurs first, 

modify each inward vent valve in accordance 

with the Accomplishment Instructions and 

Rework Instructions in Pall Corporation 

Service Bulletin SB9337–01–29–01, Issue 1, 

dated September 22, 2020 (Pall SB9337–01– 

29–01, Issue 1). 

(i) Prohibited Installation 

For all airplanes, as of the effective date of 

this AD, do not install an inward vent valve 

P/N 963.04.26.520 that has a serial number 

listed in section 1.C(1) of Pilatus SB 28–015 

on any airplane, unless it is modified in 

accordance with the Accomplishment 

Instructions and Rework Instructions of Pall 

SB9337–01–29–01, Issue 1. 

(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 certification office, 

send it to the attention of the person 

identified in paragraph (k)(1) of this AD and 

email to: 9-AVS-AIR-730-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. 


khammond on DSKJM1Z7X2PROD with RULES
Federal Register / Vol. 87, No. 64 / Monday, April 4, 2022 / Rules and Regulations 19381 

(k) Related Information 

(1) For more information about this AD, 

contact Doug Rudolph, Aviation Safety 

Engineer, General Aviation & Rotorcraft 

Section, FAA, General Aviation & Rotorcraft 

Section, International Validation Branch, 901 

Locust, Room 301, Kansas City, MO 64106; 

phone: (816) 329–4059; email: 

doug.rudolph@faa.gov. 

(2) Refer to MCAI European Union 

Aviation Safety Agency (EASA) AD 2021– 

0010, dated January 11, 2021, for related 

information. You may examine the EASA AD 

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

for and locating Docket No. Docket No. FAA– 

2021–0999. 

(l) 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) Pall Corporation Service Bulletin 

SB9337–01–29–01, Issue 1, dated September 

22, 2020. 

(ii) Pilatus Service Bulletin No. 28–015, 

dated October 12, 2020. 

(3) For service information identified in 

this AD, contact Pilatus Aircraft Ltd., CH– 

6371, Stans, Switzerland; phone: +41 848 247 

365; email: techsupport.ch@pilatusaircraft.com; website: https://www.pilatusaircraft.com/. 

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

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

ibr-locations.html. 

Issued on March 16, 2022. 

Lance T. Gant, 

Director, Compliance & Airworthiness 

Division, Aircraft Certification Service. 

[FR Doc. 2022–06975 Filed 4–1–22; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2021–1077; Project 

Identifier MCAI–2021–00607–A; Amendment 

39–21974; AD 2022–06–08] 

RIN 2120–AA64 

Airworthiness Directives; Diamond 

Aircraft Industries GmbH Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: The FAA is superseding 

Airworthiness Directive (AD) 2017–18– 

10, which applied to certain Diamond 

Aircraft Industries GmbH (DAI) Model 

DA 42, DA 42 M–NG, and DA 42 NG 

airplanes. AD 2017–18–10 required 

modifying the flap control system, 

repetitively inspecting the flap bell 

crank, and replacing the flap bell crank 

as necessary. Since the FAA issued AD 

2017–18–10, the European Union 

Aviation Safety Agency (EASA) 

superseded its mandatory continuing 

airworthiness information (MCAI) to 

correct an unsafe condition on these 

products. This AD retains the actions 

required by AD 2017–18–10, expands 

the applicability, and prohibits the 

installation of certain flap bell cranks. 

The FAA is issuing this AD to address 

the unsafe condition on these products. 

DATES: This AD is effective May 9, 2022. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of May 9, 2022. 

ADDRESSES: For service information 

identified in this final rule, contact 

Diamond Aircraft Industries GmbH, 

N.A. Otto-Stra+e 5, A–2700 Wiener 

Neustadt, Austria; phone: +43 2622 

26700; email: office@diamond-air.at; 

website: https://www.diamondaircraft.

com. You may view this service 

information at the Airworthiness 

Products Section, Operational Safety 

Branch, FAA, 901 Locust, Kansas City, 

MO 64106. For information on the 

availability of this material at the FAA, 

call (817) 222–5110. It is also available 

at https://www.regulations.gov by 

searching for and locating Docket No. 

FAA–2021–1077. 

Examining the AD Docket 

You may examine the AD docket at 

https://www.regulations.gov by 

searching for and locating Docket No. 

FAA–2021–1077; 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 MCAI, 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: 

Penelope Trease, Aviation Safety 

Engineer, General Aviation & Rotorcraft 

Section, International Validation 

Branch, FAA, 26805 E 68th Avenue, 

Denver, CO 80249; phone: (303) 342– 

1094; email: penelope.trease@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Background 

The FAA issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to supersede AD 2017–18–10, 

Amendment 39–19019 (82 FR 42029, 

September 6, 2017) (AD 2017–18–10). 

AD 2017–18–10 applied to certain 

serial-numbered DAI Model DA 42, DA 

42 M–NG, and DA 42 NG airplanes. AD 

2017–18–10 required modifying the flap 

control system by installing two spacers 

to replace a single long spacer, 

repetitively inspecting the flap bell 

crank, and replacing the flap bell crank 

with an improved part as necessary. The 

FAA issued AD 2017–18–10 to prevent 

failure of the flap bell crank, which 

could result in reduced control of the 

airplane. 

The NPRM published in the Federal 

Register on December 23, 2021 (86 FR 

72895). The NPRM was prompted by 

AD 2020–0008, dated January 20, 2020 

(referred to after this as ‘‘the MCAI’’), 

issued by EASA, which is the Technical 

Agent for the Member States of the 

European Union. The MCAI states: 

Occurrences were reported of finding 

cracks and deformation on certain flap bell 

cranks. Investigation results identified 

frequent high load conditions as the cause for 

these events. 

This condition, if not detected and 

corrected, could lead to failure of the flap 

bell crank, possibly resulting in reduced 

control of the aeroplane. 

To address this potential unsafe condition, 

DAI issued [Mandatory Service Bulletin] 

MSB 42–126/42NG–066 and the 

corresponding [Work Instructions] WI MSB 

42–126/42NG–066 (single document), 

providing inspection and modification 

instructions. Consequently, EASA issued AD 

2017–0074 to require modification of the flap 

control system by installing two spacers to 

replace a single long spacer, repetitive 

inspections of the flap bell crank, and, 

depending on findings, replacement of the 

flap bell crank with an improved part. That 

[EASA] AD also provided an optional 

terminating action by installing an improved 

flap bell crank. 

Since that [EASA] AD was issued, it was 

determined that early ‘Revisions’ of P/N 

D60–2757–11–00 flap bell cranks are no 

longer acceptable and should be removed 

from service. Prompted by that 

determination, DAI issued the applicable 

MSB, as defined in this [EASA] AD, to 

provide the relevant instructions. 

For the reason described above, this 

[EASA] AD retains the requirements of EASA 

AD 2017–0074, which is superseded, 

expands the applicability, and requires 

removal from service of certain affected parts. 

You may examine the MCAI in the 

AD docket at https://

www.regulations.gov by searching for 

and locating Docket No. FAA–2021– 

1077. 


khammond on DSKJM1Z7X2PROD with RULES