Federal Register / Vol. 85, No. 231 / Tuesday, December 1, 2020 / Rules and Regulations 76953 

(e) Reason 

This AD was prompted by a report that an 

airplane failed to extend its nose landing gear 

(NLG) using the free fall method, due to loss 

of the green hydraulic system. The FAA is 

issuing this AD to address detached magnets 

on both electrical motors of the free fall 

actuators (FFAs), which could prevent 

landing gear extension by the free fall 

method, possibly resulting in loss of control 

of the airplane after landing. 

(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 Union Aviation 

Safety Agency (EASA) AD 2020–0076, dated 

March 30, 2020 (‘‘EASA AD 2020–0076’’). 

(h) Exceptions to EASA AD 2020–0076 

(1) Where EASA AD 2020–0076 refers to its 

effective date or ‘‘the effective date of EASA 

AD 2019–0063’’ or ‘‘the effective date of 

EASA AD 2019–0164,’’ this AD requires 

using the effective date of this AD. 

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

2020–0076 does not apply to this AD. 

(3) Where paragraph (3) of EASA AD 2020– 

0076 specifies credit for certain tasks 

‘‘provided the continuity test specified in 

A330 AMM [Aircraft Maintenance Manual] 

task 32–33–00–710–809, or A340 AMM task 

32–33–00–710–806, as applicable, is 

accomplished concurrently,’’ this AD 

provides credit ‘‘provided the continuity test 

is accomplished concurrently in accordance 

with the instructions of an FAA-approved 

maintenance or inspection program.’’ 

(i) No Reporting Requirement 

Although the service information 

referenced in EASA AD 2020–0076 specifies 

to submit certain information to the 

manufacturer, this AD does not include that 

requirement. 

(j) Other FAA AD Provisions 

The following provisions also apply to this 

AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, Large Aircraft 

Section, 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 responsible Flight 

Standards Office, as appropriate. If sending 

information directly to the Large Aircraft 

Section, 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. Before using any 

approved AMOC, notify your appropriate 

principal inspector, or lacking a principal 

inspector, the manager of the responsible 

Flight Standards Office. 

(2) Contacting the Manufacturer: For any 

requirement in this AD to obtain instructions 

from a manufacturer, the instructions must 

be accomplished using a method approved 

by the Manager, Large Aircraft Section, 

International Validation Branch, FAA; or 

EASA; or Airbus SAS’s EASA Design 

Organization Approval (DOA). If approved by 

the DOA, the approval must include the 

DOA-authorized signature. 

(3) Required for Compliance (RC): For any 

service information referenced in EASA AD 

2020–0076 that contains RC procedures and 

tests: Except as required by paragraphs (h)(3) 

and (j)(2) of this AD, RC procedures and tests 

must be done to comply with this AD; any 

procedures or tests that are not identified as 

RC are recommended. Those procedures and 

tests that are not identified as RC may be 

deviated from using accepted methods in 

accordance with the operator’s maintenance 

or inspection program without obtaining 

approval of an AMOC, provided the 

procedures and tests identified as RC can be 

done and the airplane can be put back in an 

airworthy condition. Any substitutions or 

changes to procedures or tests identified as 

RC require approval of an AMOC. 

(k) Related Information 

For more information about this AD, 

contact Vladimir Ulyanov, Aerospace 

Engineer, Large Aircraft Section, 

International Validation Branch, FAA, 2200 

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

telephone and fax 206–231–3229; email 

vladimir.ulyanov@faa.gov. 

(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 this AD specifies otherwise. 

(i) European Union Aviation Safety Agency 

(EASA) AD 2020–0076, dated March 30, 

2020. 

(ii) [Reserved] 

(3) For EASA AD 2020–0076, 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 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 on the internet at https:// 

www.regulations.gov by searching for and 

locating Docket No. FAA–2019–0484. 

(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 November 18, 2020. 

Lance T. Gant, 

Director, Compliance & Airworthiness 

Division, Aircraft Certification Service. 

[FR Doc. 2020–26435 Filed 11–30–20; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2020–0712; Product 

Identifier 2019–CE–013–AD; Amendment 

39–21339; AD 2020–24–09] 

RIN 2120–AA64 

Airworthiness Directives; Piper 

Aircraft, Inc. Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: The FAA is adopting a new 

airworthiness directive (AD) for certain 

Piper Aircraft, Inc., Model PA–34–220T 

airplanes. This AD was prompted by a 

report of damage to the rudder flight 

control cables and the emergency power 

supply (EPS) system wiring due to 

inadequate clearance from the EPS 

wiring harness. This AD requires 

inspecting the rudder flight control 

cables and the EPS wiring for damage, 

replacing damaged cables and wires if 

necessary, and re-routing the EPS wiring 

harness to ensure proper clearance 

between the EPS and the rudder flight 

control cables. The FAA is issuing this 

AD to address the unsafe condition on 

these products. 

DATES: This AD is effective January 5, 

2021. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of January 5, 2021. 

ADDRESSES: Piper Aircraft, Inc., 2916 

Piper Drive, Vero Beach, Florida 32960; 

telephone: (772) 567–4361; email: 

customer.service@piper.com; internet: 

https://www.piper.com. You may view 

this referenced service information at 

the FAA, Airworthiness Products 

Section, Operational Safety Branch, 901 

Locust, Kansas City, Missouri 64106. 

For information on the availability of 

this material at the FAA, call (816) 329– 

4148. 

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– 

0712; or in person at Docket Operations 


khammond on DSKJM1Z7X2PROD with RULES3
76954 Federal Register / Vol. 85, No. 231 / Tuesday, December 1, 2020 / Rules and Regulations 

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: 

Bryan Long, Aerospace Engineer, 

Atlanta ACO Branch, FAA, 1701 

Columbia Avenue, College Park, Georgia 

30337; phone: (404) 474–5578; fax: (404) 

474–5606; email: bryan.long@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Discussion 

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 Piper 

Aircraft, Inc., Model PA–34–220T 

airplanes. The NPRM published in the 

Federal Register on July 28, 2020 (85 FR 

45353). The NPRM was prompted by a 

report of damage to the rudder flight 

control cables and the EPS system 

wiring due to inadequate clearance from 

the EPS wiring harness. Use of the 

rudder flight control cable and the 

motion of the cable rubbing against the 

EPS wiring can wear through the rudder 

flight control cable insulation and cause 

an electrical path to ground. The flow of 

the electrical current can burn (arc) 

through the rudder flight control cable 

strands, eventually severing the rudder 

flight control cable. In the NPRM, the 

FAA proposed to require inspecting the 

rudder flight control cables and the EPS 

wiring for damage, replacing damaged 

cables and wires if necessary, and rerouting the EPS wiring harness to 

ensure proper clearance between the 

EPS and the rudder flight control cables. 

This condition, if not addressed, 

could result in electrical arcing between 

the EPS and the rudder flight control 

cables with consequent failure of the 

rudder flight control system. This 

failure could cause loss of yaw control 

and lead to loss of control of the 

airplane during an engine out 

condition/operation. The FAA is issuing 

this AD to address the unsafe condition 

on these products. 

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 

adopting this AD as proposed in the 

NPRM. Accordingly, the FAA is issuing 

this AD to address the unsafe condition 

on these products. 

Related Service Information Under 1 

CFR Part 51 

The FAA reviewed Piper Aircraft, 

Inc., Service Bulletin No. 1337, dated 

February 15, 2019. The service bulletin 

contains procedures for inspecting the 

rudder flight control cables and the EPS 

wiring for damage, replacing damaged 

cables and wires, and re-routing the EPS 

wiring harness to the opposite side of 

the EPS bracket to improve clearance 

from the rudder flight control cable. 

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. 

Costs of Compliance 

The FAA estimates that this AD 

affects 25 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 

Inspect the rudder flight control cables and 

the EPS wiring.

1 work-hour × $85 per hour = $85 ................. Not applicable $85 $2,125 

Re-routing the EPS wiring harness ................ 2 work-hours × $85 per hour = $170 ............. $100 ............... 270 6,750 

The FAA estimates the following 

costs to do any necessary replacements 

that would be required based on the 

results of the inspection. The FAA has 

no way of determining the number of 

airplanes that might need actions: 

ON-CONDITION COSTS

Action Labor cost Parts cost Cost per 

product 

Replace damaged rudder flight control cable .............. 8 work-hours × $85 per hour = $680 ........................... $157 $837 

Replace damaged EPS wiring ..................................... 10 work-hours × $85 per hour = $850 ......................... 2,770 3,620 

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 


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Federal Register / Vol. 85, No. 231 / Tuesday, December 1, 2020 / Rules and Regulations 76955 

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: 

2020–24–09 Piper Aircraft, Inc.: 

Amendment 39–21339; Docket No. 

FAA–2020–0712; Product Identifier 

2019–CE–013–AD. 

(a) Effective Date 

This airworthiness directive (AD) is 

effective January 5, 2021. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to Piper Aircraft, Inc., 

Model PA–34–220T airplanes, serial numbers 

3449459 and 3449467 through 3449508, 

certificated in any category. 

(d) Subject 

Joint Aircraft System Component (JASC)/ 

Air Transport Association (ATA) of America 

Code 27. Flight Controls. 

(e) Unsafe Condition 

This AD was prompted by a report of 

damage to the rudder flight control cables 

and the emergency power supply (EPS) 

system wiring due to inadequate clearance 

from the EPS wiring harness. The FAA is 

issuing this AD to detect, correct, and 

prevent damaged rudder flight control cables 

and EPS system wiring. The unsafe 

condition, if not addressed, could result in 

electrical arcing between the EPS and the 

rudder flight control cables with consequent 

failure of the rudder flight control system. 

This failure could cause loss of yaw control 

and lead to loss of control of the airplane 

during an engine out condition/operation. 

(f) Compliance 

Unless already done, comply with this AD 

within 50 hours time-in-service after the 

effective date of this AD or within 6 months 

after the effective date of this AD, whichever 

occurs first. 

(g) Inspect, Replace, and Relocate 

(1) Inspect the rudder flight control cables 

and the EPS wiring for chafing and damage 

by following step 3 of the Instructions in 

Piper Service Bulletin No. 1337, dated 

February 15, 2019 (Piper SB No. 1337). If 

there is any chafing or damage, before further 

flight, replace the rudder flight control cable 

and EPS wiring. 

(2) Relocate the EPS wiring harness by 

following steps 4 through 12 of the 

Instructions in Piper SB No. 1337. 

(h) 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 paragraph (i) of this 

AD. 

(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) For service information that contains 

steps that are labeled as Required for 

Compliance (RC), the following provisions 

apply. 

(i) The steps labeled as RC, including 

substeps under an RC step and any figures 

identified in an RC step, must be done to 

comply with the AD. An AMOC is required 

for any deviations to RC steps, including 

substeps and identified figures. 

(ii) Steps not labeled as RC may be 

deviated from using accepted methods in 

accordance with the operator’s maintenance 

or inspection program without obtaining 

approval of an AMOC, provided the RC steps, 

including substeps and identified figures, can 

still be done as specified, and the airplane 

can be put back in an airworthy condition. 

(i) Related Information 

For more information about this AD, 

contact Bryan Long, Aerospace Engineer, 

Atlanta ACO Branch, FAA, 1701 Columbia 

Avenue, College Park, Georgia 30337; phone: 

(404) 474–5578; fax: (404) 474–5606; email: 

bryan.long@faa.gov. 

(j) Material Incorporated by Reference 

(1) The Director of the Federal Register 

approved the incorporation by reference of 

the service information listed in this 

paragraph under 5 U.S.C. 552(a) and 1 CFR 

part 51. 

(2) You must use this service information 

as applicable to do the actions required by 

this AD, unless the AD specifies otherwise. 

(i) Piper Service Bulletin No. 1337, dated 

February 15, 2019. 

(ii) [Reserved] 

(3) For the service information identified in 

this AD, contact Piper Aircraft, Inc., 2916 

Piper Drive, Vero Beach, Florida 32960; 

telephone: (772) 567–4361; email: 

customer.service@piper.com; internet: 

https://www.piper.com. 

(4) You may view this service information 

at FAA, Airworthiness Products Section, 

Operational Safety Branch, 901 Locust, 

Kansas City, Missouri 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 November 17, 2020. 

Lance T. Gant, 

Director, Compliance & Airworthiness 

Division, Aircraft Certification Service. 

[FR Doc. 2020–26473 Filed 11–30–20; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2020–1027; Project 

Identifier MCAI–2020–01375–R; Amendment 

39–21333; AD 2020–24–03] 

RIN 2120–AA64 

Airworthiness Directives; Airbus 

Helicopters 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule; request for 

comments. 

SUMMARY: The FAA is adopting a new 

airworthiness directive (AD) for Airbus 

Helicopters Model AS350B, AS350BA, 

AS350B1, AS350B2, AS350D, AS355E, 

AS355F, AS355F1, and AS355F2 

helicopters. This AD requires testing the 

UP/DOWN switches of a certain partnumbered DUNLOP cyclic stick grip, 

installing a placard, and revising the 

existing Rotorcraft Flight Manual (RFM) 

for your helicopter, or removing the 

DUNLOP cyclic stick grip. This AD was 

prompted by an inadvertent activation 

of the rescue hoist cable cutter. The 

actions of this AD are intended to 

address an unsafe condition on these 

products. 

DATES: This AD becomes effective 

December 16, 2020. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain documents listed in this AD 

as of December 16, 2020. 

The FAA must receive comments on 

this AD by January 15, 2021. 

ADDRESSES: You may send comments by 

any of the following methods: 

• Federal eRulemaking Docket: Go to 

https://www.regulations.gov. Follow the 

online instructions for sending your 

comments electronically. 

• Fax: 202–493–2251. 


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