Federal Register / Vol. 86, No. 43 / Monday, March 8, 2021 / Proposed Rules 13225 

the existing maintenance manual or ICA for 

your airplane as follows: 

(i) Replace the ALS with the Airworthiness 

Limitations Section of Pilatus PC–6 

Airworthiness Limitations Document No. 

02334, Revision 10, dated October 30, 2020. 

(ii) Add (or replace, if applicable) 

Appendix K, Fuselage Wing Fittings— 

Inspection/Check, of Pilatus PC 6 

Airworthiness Limitations Document No. 

02334, Revision 10, dated October 30, 2020. 

(iii) Add Appendix L, Wing to Fuselage 

Fittings—Inspection/Check, of Pilatus PC 6 

Airworthiness Limitations Document No. 

02334, Revision 9, dated March 6, 2020. 

(3) For all airplanes specified in paragraph 

(c) of this AD, after revising the ALS as 

required by paragraphs (f)(1) and (2) of this 

AD, remove from service each part that has 

reached or exceeded its new life limit. 

(g) Inspections and Replacement 

(1) For airplanes with a bush part number 

(P/N) 6100.0020.01 that has been bonded as 

specified in Section 53–00–01, Fuselage 

Wing Fittings—Inspection/Check, of Pilatus 

PC–6 Aircraft Maintenance Manual 

Document No. 01975, Revision 29, dated 

February 28, 2020; or Appendix K, Fuselage 

Wing Fittings—Inspection/Check, of Pilatus 

PC–6 Airworthiness Limitations Document 

No. 02334, Revision 9, dated March 6, 2020: 

Within 50 hours time-in-service (TIS) after 

the effective date of this AD, perform a visual 

and eddy current inspection of each fuselage 

wing fitting on fuselage Frame 3, remove 

bush P/N 6100.0020.01 from service, and 

install a new (zero hours TIS) bush P/N 

6100.0020.01 into Frame 3 with grease by 

using the procedures specified in paragraph 

(f)(1)(ii) or (f)(2)(ii) of this AD, as applicable 

to your airplane. 

(2) Unless already done, within 1,100 

hours TIS after the effective date of this AD 

or within 12 months after the effective date 

of this AD, whichever occurs first, perform 

an eddy current inspection of each fuselage 

wing fitting and each wing-to-fuselage fitting 

using the procedures specified in paragraphs 

(f)(1)(ii) and (iii) of this AD, or paragraphs 

(f)(2)(ii) and (iii) of this AD, as applicable to 

your airplane. Thereafter, repeat the eddy 

current inspection of each fuselage wing 

fitting and each wing-to-fuselage fitting at the 

intervals specified in the ALS identified in 

paragraph (f)(1)(i) or (f)(2)(i), as applicable to 

your airplane. 

(h) No Alternative Actions or Intervals 

After the ALS has been revised as required 

by paragraph (f) of this AD, no alternative 

inspection intervals or procedures may be 

approved, except as provided in paragraph (i) 

of this AD. 

(i) Other FAA AD Provisions 

Alternative Methods of Compliance 

(AMOCs): 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. 

Send your request to the person identified in 

Related Information. Before using any 

approved AMOC, notify your appropriate 

principal inspector, or lacking a principal 

inspection, the manager of the local Flight 

Standards District Office. 

(j) Related Information 

(1) Refer to Mandatory Continuing 

Airworthiness Information (MCAI) European 

Union Aviation Safety Agency (EASA) AD 

No. 2020–0120, dated May 27, 2020, and 

EASA AD No. 2020–0278, dated December 

14, 2020, for related information. This MCAI 

may be found in the AD docket on the 

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

searching for and locating Docket No. FAA– 

2020–0857. 

(2) For more information about this AD, 

contact Doug Rudolph, Aviation Safety 

Engineer, FAA, General Aviation & Rotorcraft 

Section, International Validation Branch, 901 

Locust, Room 301, Kansas City, MO 64106; 

telephone: (816) 329–4059; fax: (816) 329– 

4090; email: doug.rudolph@faa.gov. 

(3) For service information identified in 

this AD, contact Pilatus Aircraft Ltd., 

Customer Support General Aviation, CH– 

6371 Stans, Switzerland; telephone: +41 848 

24 7 365; email: Techsupport@

pilatusaircraft.com; internet: https://

www.pilatusaircraft.com/en. You may view 

this service information at the FAA, 

Airworthiness Products Section, Operational 

Safety Branch, 901 Locust, Kansas City, MO 

64106. For information on the availability of 

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

Issued on February 25, 2021. 

Gaetano A. Sciortino, 

Deputy Director for Strategic Initiatives, 

Compliance & Airworthiness Division, 

Aircraft Certification Service. 

[FR Doc. 2021–04395 Filed 3–5–21; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2021–0129; Project 

Identifier AD–2020–01597–E] 

RIN 2120–AA64 

Airworthiness Directives; International 

Aero Engines AG Turbofan Engines 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: The FAA proposes to adopt a 

new airworthiness directive (AD) for 

certain International Aero Engines AG 

(IAE) V2522–A5, V2524–A5, V2525–D5, 

V2527–A5, V2527E–A5, V2527M–A5, 

V2528–D5, V2530–A5, V2531–E5, and 

V2533–A5 model turbofan engines. This 

proposed AD was prompted by an 

analysis performed by the manufacturer 

after an event involving an uncontained 

failure of a high-pressure turbine (HPT) 

1st-stage disk that resulted in highenergy debris penetrating the engine 

cowling. This proposed AD would 

require the performance of an ultrasonic 

inspection (USI) of the HPT 1st-stage 

disk and HPT 2nd-stage disk and, 

depending on the results of the 

inspections, replacement of the HPT 1ststage disk or HPT 2nd-stage disk. The 

FAA is proposing this AD to address the 

unsafe condition on these products. 

DATES: The FAA must receive comments 

on this proposed AD by April 7, 2021. 

ADDRESSES: You may send comments, 

using the procedures found in 14 CFR 

11.43 and 11.45, by any of the following 

methods: 

• Federal eRulemaking Portal: Go to 

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

instructions for submitting comments. 

• Fax: (202) 493–2251. 

• Mail: U.S. Department of 

Transportation, Docket Operations, 

M–30, West Building Ground Floor, 

Room W12–140, 1200 New Jersey 

Avenue SE, Washington, DC 20590. 

• Hand Delivery: Deliver to Mail 

address above between 9 a.m. and 5 

p.m., Monday through Friday, except 

Federal holidays. 

For service information identified in 

this NPRM, contact International Aero 

Engines AG, 400 Main Street, East 

Hartford, CT 06118; phone: (800) 565– 

0140; email: help24@pw.utc.com; 

website: http://fleetcare.pw.utc.com. 

You may view this service information 

at the FAA, Airworthiness Products 

Section, Operational Safety Branch, 

1200 District Avenue, Burlington, MA 

01803. For information on the 

availability of this material at the FAA, 

call (781) 238–7759. 

Examining the AD Docket 

You may examine the AD docket at 

https://www.regulations.gov by 

searching for and locating Docket No. 

FAA–2021–0129; 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 

NPRM, any comments received, and 

other information. The street address for 

Docket Operations is listed above. 

FOR FURTHER INFORMATION CONTACT: 

Nicholas Paine, Aviation Safety 

Engineer, ECO Branch, FAA, 1200 

District Avenue, Burlington, MA 01803; 

phone: (781) 238–7742; fax: (781) 238– 

7199; email: nicholas.j.paine@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Comments Invited 

The FAA invites you to send any 

written relevant data, views, or 

arguments about this proposal. Send 

your comments to an address listed 

under ADDRESSES. Include ‘‘Docket No. 

FAA–2021–0129; Project Identifier AD– 

2020–01597–E’’ at the beginning of your 

comments. The most helpful comments 


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reference a specific portion of the 

proposal, explain the reason for any 

recommended change, and include 

supporting data. The FAA will consider 

all comments received by the closing 

date and may amend this proposal 

because of those comments. 

The FAA has been informed that IAE 

has done some outreach with affected 

operators regarding the proposed 

corrective actions for this unsafe 

condition. As a result, affected operators 

are already aware of the proposed 

corrective actions and, in some cases, 

have already begun planning for 

implementation. Therefore, the FAA has 

determined that a 30-day comment 

period is appropriate given the 

particular circumstances related to the 

proposed correction of this unsafe 

condition. 

Except for Confidential Business 

Information (CBI) as described in the 

following paragraph, and other 

information as described in 14 CFR 

11.35, the FAA will post all comments 

received, without change, to https://

www.regulations.gov, including any 

personal information you provide. The 

agency will also post a report 

summarizing each substantive verbal 

contact received about this NPRM. 

Confidential Business Information 

CBI is commercial or financial 

information that is both customarily and 

actually treated as private by its owner. 

Under the Freedom of Information Act 

(FOIA) (5 U.S.C. 552), CBI is exempt 

from public disclosure. If your 

comments responsive to this NPRM 

contain commercial or financial 

information that is customarily treated 

as private, that you actually treat as 

private, and that is relevant or 

responsive to this NPRM, it is important 

that you clearly designate the submitted 

comments as CBI. Please mark each 

page of your submission containing CBI 

as ‘‘PROPIN.’’ The FAA will treat such 

marked submissions as confidential 

under the FOIA, and they will not be 

placed in the public docket of this 

NPRM. Submissions containing CBI 

should be sent to Nicholas Paine, 

Aviation Safety Engineer, ECO Branch, 

FAA, 1200 District Avenue, Burlington, 

MA 01803. Any commentary that the 

FAA receives which is not specifically 

designated as CBI will be placed in the 

public docket for this rulemaking. 

Background 

On March 18, 2020, an Airbus Model 

A321–231 airplane, powered by IAE 

V2533–A5 model turbofan engines, 

experienced an uncontained HPT 1ststage disk failure that resulted in an 

aborted takeoff. The uncontained failure 

of the HPT 1st-stage disk resulted in 

high-energy debris penetrating the 

engine cowling. The FAA published 

Emergency AD 2020–07–51 on March 

21, 2020 (followed by publication in the 

Federal Register on April 13, 2020, as 

a Final Rule, Request for Comments (85 

FR 20402)) and AD 2021–01–03 on 

January 6, 2021 (86 FR 458), to remove 

from service HPT 1st-stage and HPT 

2nd-stage disks identified as having the 

highest risk of failure. Based on the root 

cause analysis performed since that 

event, the manufacturer identified a 

population of HPT 1st-stage disks and 

HPT 2nd-stage disks that require 

inspection and possible removal from 

service. This condition, if not 

addressed, could result in uncontained 

HPT disk failure, damage to the engine, 

damage to the airplane, and loss of the 

airplane. 

FAA’s Determination 

The FAA is issuing this NPRM after 

determining that the unsafe condition 

described previously is likely to exist or 

develop on other products of the same 

type design. 

Related Service Information Under 1 

CFR Part 51 

The FAA reviewed IAE NonModification Service Bulletin (NMSB) 

No. V2500–ENG–72–0713, Revision 1, 

dated January 26, 2021. The NMSB 

identifies the affected HPT 1st-stage 

disks and HPT 2nd-stage disks on IAE 

V2522–A5, V2524–A5, V2525–D5, 

V2527–A5, V2527E–A5, V2527M–A5, 

V2528–D5, V2530–A5, and V2533–A5 

model turbofan engines and specifies 

procedures for a USI of the HPT 1ststage disk and HPT 2nd-stage disk. 

The FAA also reviewed IAE NMSB 

No. V2500–E5–72–0015, dated 

December 15, 2020. The NMSB 

identifies the affected HPT 1st-stage 

disks and HPT 2nd-stage disks on IAE 

V2531–E5 model turbofan engines and 

specifies procedures for a USI of the 

HPT 1st-stage disk and HPT 2nd-stage 

disk. 

This service information is reasonably 

available because the interested parties 

have access to it through their normal 

course of business or by the means 

identified in ADDRESSES. 

Proposed AD Requirements in This 

NPRM 

This proposed AD would require the 

performance of a USI of the HPT 1ststage disk and HPT 2nd-stage disk and, 

depending on the results of the 

inspections, replacement of the HPT 1ststage disk or HPT 2nd-stage disk with a 

part eligible for installation. 

Costs of Compliance 

The FAA estimates that this AD, if 

adopted as proposed, would affect 1,100 

engines installed on airplanes of U.S. 

registry. 

The FAA estimates the following 

costs to comply with this proposed AD: 

ESTIMATED COSTS

Action Labor cost Parts cost Cost per 

product 

Cost on U.S. 

operators 

USI the HPT 1st-stage disk and HPT 2ndstage disk.20 work-hours × $85 per hour = $1,700 ........ $0 $1,700 $1,870,000 

The FAA estimates the following 

costs to do any necessary replacement 

that would be required based on the 

results of the proposed inspections. The 

agency has no way of determining the 

number of aircraft that might need this 

replacement: 


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Federal Register / Vol. 86, No. 43 / Monday, March 8, 2021 / Proposed Rules 13227 

ON-CONDITION COSTS

Action Labor cost Parts cost Cost per 

product 

Replace the HPT 1st-stage disk or HPT 2nd-stage 

disk.

0 work-hours × $85 per hour = $0 ............................... $300,000 $300,000 

The FAA has included all known 

costs in its cost estimate. According to 

the manufacturer, however, some of the 

costs of this proposed 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 

The FAA determined that this 

proposed AD would not have federalism 

implications under Executive Order 

13132. This proposed AD would 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 proposed regulation: 

(1) Is not a ‘‘significant regulatory 

action’’ under Executive Order 12866, 

(2) Would not affect intrastate 

aviation in Alaska, and 

(3) Would 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 Proposed Amendment 

Accordingly, under the authority 

delegated to me by the Administrator, 

the FAA proposes to amend 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: 

International Aero Engines AG: Docket No. 

FAA–2021–0129; Project Identifier AD– 

2020–01597–E. 

(a) Comments Due Date 

The FAA must receive comments on this 

airworthiness directive (AD) by April 7, 

2021. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to International Aero 

Engines AG (IAE) V2522–A5, V2524–A5, 

V2525–D5, V2527–A5, V2527E–A5, 

V2527M–A5, V2528–D5, V2530–A5, V2531– 

E5, and V2533–A5 model turbofan engines 

with an installed: 

(1) High-pressure turbine (HPT) 1st-stage 

disk, part number (P/N) 2A5001, with a serial 

number (S/N) listed in Appendix A, Table 1, 

of IAE Non-Modification Service Bulletin 

(NMSB) No. V2500–ENG–72–0713, Revision 

1, dated January 26, 2021 (IAE NMSB V2500– 

ENG–72–0713, Revision 1) or IAE NMSB No. 

V2500–E5–72–0015, dated December 15, 

2020 (IAE NMSB V2500–E5–72–0015); and/ 

or 

(2) HPT 2nd-stage disk, P/N 2A4802, with 

an S/N listed in Appendix A, Table 2, of IAE 

NMSB V2500–ENG–72–0713, Revision 1, or 

IAE NMSB V2500–E5–72–0015. 

(d) Subject 

Joint Aircraft System Component (JASC) 

Code 7250, Turbine Section. 

(e) Unsafe Condition 

This AD was prompted by an analysis 

performed by the manufacturer after an event 

involving an uncontained failure of a HPT 

1st-stage disk that resulted in high-energy 

debris penetrating the engine cowling. The 

FAA is issuing this AD to prevent failure of 

the HPT 1st-stage disk and HPT 2nd-stage 

disk. The unsafe condition, if not addressed, 

could result in uncontained HPT disk failure, 

damage to the engine, damage to the airplane, 

and loss of the airplane. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Required Actions 

(1) For IAE V2527E–A5, V2527M–A5, 

V2528–D5, V2530–A5, and V2533–A5 model 

turbofan engines with an HPT 1st-stage disk, 

P/N 2A5001, with an S/N listed in Appendix 

A, Table 1, of IAE NMSB V2500–ENG–72– 

0713, Revision 1, at the next engine shop 

visit after the effective date of this AD or 

before the HPT 1st-stage disk has 

accumulated 3,200 flight cycles (FCs) since 

the effective date of this AD, whichever 

occurs first, perform an ultrasonic inspection 

(USI) of the HPT 1st-stage disk using the 

Accomplishment Instructions, paragraph 6, 

of IAE NMSB V2500–ENG–72–0713, 

Revision 1. 

(2) For IAE V2527E–A5, V2527M–A5, 

V2528–D5, V2530–A5, and V2533–A5 model 

turbofan engines with an HPT 2nd-stage disk, 

P/N 2A4802, with an S/N listed in Appendix 

A, Table 2, of IAE NMSB V2500–ENG–72– 

0713, Revision 1, at the next engine shop 

visit after the effective date of this AD or 

before the HPT 2nd-stage disk has 

accumulated 3,200 FCs since the effective 

date of this AD, whichever occurs first, 

perform a USI of the HPT 2nd-stage disk 

using the Accomplishment Instructions, 

paragraph 7, of IAE NMSB V2500–ENG–72– 

0713, Revision 1. 

(3) For IAE V2522–A5, V2524–A5, V2525– 

D5, and V2527–A5 model turbofan engines 

with an HPT 1st-stage disk, P/N 2A5001, 

with an S/N listed in Appendix A, Table 1, 

of IAE NMSB V2500–ENG–72–0713, 

Revision 1, at the next HPT rotor and stator 

assembly (HPT module) removal or before 

the HPT 1st-stage disk has accumulated 6,700 

FCs since the effective date of this AD, 

whichever occurs first, perform a USI of the 

HPT 1st-stage disk using the 

Accomplishment Instructions, paragraph 6, 

of IAE NMSB V2500–ENG–72–0713, 

Revision 1. 

(4) For IAE V2522–A5, V2524–A5, V2525– 

D5, and V2527–A5 model turbofan engines 

with an HPT 2nd-stage disk, P/N 2A4802, 

with an S/N listed in Appendix A, Table 2, 

of IAE NMSB V2500–ENG–72–0713, 

Revision 1, at the next HPT module removal 

or before the HPT 2nd-stage disk has 

accumulated 6,700 FCs since the effective 

date of this AD, whichever occurs first, 

perform a USI of the HPT 2nd-stage disk 

using the Accomplishment Instructions, 

paragraph 7, of IAE NMSB V2500–ENG–72– 

0713, Revision 1. 

(5) For IAE V2531–E5 model turbofan 

engines with an HPT 1st-stage disk, P/N 


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2A5001, with an S/N listed in Appendix A, 

Table 1, of IAE NMSB V2500–E5–72–0015, at 

the next engine shop visit or before the HPT 

1st-stage disk has accumulated 3,200 FCs 

since the effective date of this AD, whichever 

occurs first, perform a USI of the HPT 1ststage disk using the Accomplishment 

Instructions, paragraph 6, of IAE NMSB 

V2500–E5–72–0015. 

(6) For IAE V2531–E5 model turbofan 

engines with an HPT 2nd-stage disk, P/N 

2A4802, with an S/N listed in Appendix A, 

Table 2, of IAE NMSB V2500–E5–72–0015, at 

the next engine shop visit or before the HPT 

2nd-stage disk has accumulated 3,200 FCs 

since the effective date of this AD, whichever 

occurs first, perform a USI of the HPT 2ndstage disk using the Accomplishment 

Instructions, paragraph 7, of IAE NMSB 

V2500–E5–72–0015. 

(7) If, during the USI required by 

paragraphs (g)(1) through (6) of this AD, a 

HPT 1st-stage disk or HPT 2nd-stage disk 

does not pass the inspection as specified in 

the Accomplishment Instructions, paragraph 

8., of IAE NMSB V2500–ENG–72–0713, 

Revision 1, or IAE NMSB V2500–E5–72– 

0015, as applicable, before further flight, 

remove the HPT 1st-stage disk or 2nd-stage 

disk, as applicable, from service and replace 

with a part eligible for installation. 

(h) Definition 

For the purpose of this AD, an ‘‘engine 

shop visit’’ is the induction of an engine into 

the shop for maintenance involving the 

separation of pairs of major mating engine 

flanges, H–P, except for the following 

situations, which do not constitute an engine 

shop visit. 

(1) Separation of engine flanges solely for 

the purposes of transportation without 

subsequent engine maintenance. 

(2) Engine removal for the purpose of 

performing field maintenance activities at a 

maintenance facility in lieu of performing 

them on-wing. 

(i) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, ECO Branch, FAA, has 

the authority to approve AMOCs for this AD, 

if requested using the procedures found in 14 

CFR 39.19. In accordance with 14 CFR 39.19, 

send your request to your principal inspector 

or local Flight Standards District Office, as 

appropriate. If sending information directly 

to the manager of the certification office, 

send it to the attention of the person 

identified in Related Information. You may 

email your request to: ANE-AD-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 

(1) For more information about this AD, 

contact Nicholas Paine, Aviation Safety 

Engineer, ECO Branch, FAA, 1200 District 

Avenue, Burlington, MA 01803; phone: (781) 

238–7742; fax: (781) 238–7199; email: 

nicholas.j.paine@faa.gov. 

(2) For service information identified in 

this AD, contact International Aero Engines 

AG, 400 Main Street, East Hartford, CT 

06118; phone: (800) 565–0140; email: 

help24@pw.utc.com; website: http://

fleetcare.pw.utc.com. You may view this 

referenced service information at the FAA, 

Airworthiness Products Section, Operational 

Safety Branch, 1200 District Avenue, 

Burlington, MA 01803. For information on 

the availability of this material at the FAA, 

call (781) 238–7759. 

Issued on February 24, 2021. 

Gaetano A. Sciortino, 

Deputy Director for Strategic Initiatives, 

Compliance & Airworthiness Division, 

Aircraft Certification Service. 

[FR Doc. 2021–04236 Filed 3–5–21; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2007–27495; Project 

Identifier 2005–SW–14–AD] 

RIN 2120–AA64 

Airworthiness Directives; Eurocopter 

France Helicopters 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Proposed rule; withdrawal. 

SUMMARY: The FAA is withdrawing a 

notice of proposed rulemaking (NPRM) 

that proposed to adopt a new 

airworthiness directive (AD) that would 

have applied to certain Eurocopter 

France (now Airbus Helicopters) Model 

AS350B, BA, B1, B2, B3, C, D, and D1; 

EC–130B4; and AS355E, F, F1, F2, and 

N helicopters. The NPRM would have 

required modifying the collective holddown strap (strap) and thereafter 

inspecting it at specified intervals to 

ensure the rubber grommet is resting 

against the console or replacing the 

strap with a strap that has a torsional 

spring at the lower end of the strap. 

Since issuance of the NPRM, the FAA 

issued AD 2014–02–05, which 

addresses the unsafe condition 

identified in the NPRM. Accordingly, 

the NPRM is withdrawn. 

DATES: As of March 8, 2021, the 

proposed rule, which was published in 

the Federal Register on March 13, 2007 

(72 FR 11297), is withdrawn. 

ADDRESSES: 

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–2007– 

27495; 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 

AD action, any comments received, and 

other information. The street 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: 

Vince Massey, Aerospace Engineer, 

Systems and Equipment Section, FAA, 

Seattle ACO Branch, 2200 South 216th 

St., Des Moines, WA 98198; phone and 

fax: 206–231–3545; email: 

vince.massey@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Discussion 

The FAA issued an NPRM that 

proposed to amend 14 CFR part 39 by 

adding an AD that would have applied 

to the specified products. The NPRM 

was published in the Federal Register 

on March 13, 2007 (72 FR 11297). The 

NPRM was prompted by reports of two 

accidents occurring while the pilots 

were performing an autorotation. The 

pilots were unable to arrest the descent 

of the helicopter using collective blade 

pitch due to the collective stick locking 

in the down position when the 

collective was lowered during the 

maneuver. The NPRM proposed to 

require modifying the strap and 

thereafter inspecting it at specified 

intervals to ensure the rubber grommet 

is resting against the console or 

replacing the strap with a strap that has 

a torsional spring at the lower end of the 

strap. 

Actions Since the NPRM Was Issued 

Since issuance of the NPRM, the FAA 

has published AD 2014–02–05, 

Amendment 39–17733 (79 FR 5251, 

January 31, 2014) (AD 2014–02–05), 

which addresses the unsafe condition 

for Model AS350B, BA, B1, B2, B3, C, 

D, and D1 helicopters identified in the 

NPRM. The FAA also determined that 

the Model EC–130B4 helicopters and 

Model AS355E, F, F1, F2, and N 

helicopters identified in the NPRM are 

not affected by the unsafe condition 

because the root cause of the unsafe 

condition is certain collective straps 

that are only installed on the Model 

AS350B, BA, B1, B2, B3, C, D, and D1 

helicopters. Therefore, the FAA has 

determined that this AD action is not 

appropriate. 

AD 2014–02–05 includes certain 

helicopters that were not included in 

the NPRM. Although the NPRM applied 

only to helicopters with a certain partnumbered hold-down strap, AD 2014– 

02–05 applies to Model AS350B, BA, 


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