48080 Federal Register / Vol. 86, No. 164 / Friday, August 27, 2021 / Proposed Rules 

of 5,000 hours TIS to the total hours TIS 

indicated on the component history card or 

equivalent record for the collective lever P/ 

N 412–010–408–101. 

Note 1 to paragraph (g)(1)(i): Bell 

Helicopter service information identifies 

helicopters with serial numbers 36570, 

36579, 36587, and 36593 through 36602 

inclusive, as helicopters originally delivered 

with a Strake and FastFin system installed. 

(ii) For helicopters with a Strake and 

FastFin system P/N 412–705–040–101 

installed after delivery from the 

manufacturer, add a permanent penalty of 

50% of the total hours TIS accumulated by 

the collective lever P/N 412–010–408–101 on 

the component history card or equivalent 

record for the collective lever P/N 412–010– 

408–101. 

Note 2 to paragraph (g)(1)(ii): The 

Accomplishment Instructions, part II, 

paragraph 2., of Bell Helicopter Alert Service 

Bulletin 412–12–151, Revision A, dated July 

8, 2014, provides an example of calculating 

and adding a permanent penalty of 50%. 

(iii) For helicopters without a Strake and 

FastFin system P/N 412–705–040–101 

installed, but with a collective lever P/N 

412–010–408–101 installed, add a permanent 

penalty of 50% of the total hours TIS 

accumulated by the collective lever on the 

component history card or equivalent record 

for the collective lever. 

(2) Before further flight, remove from 

service any collective lever P/N 412–010– 

408–101 that has reached or exceeded its life 

limit of 10,000 total hours TIS. Thereafter, 

remove from service each collective lever P/ 

N 412–010–408–101 on or before reaching its 

life limit of 10,000 total hours TIS. 

(3) As of the effective date of this AD, do 

not install a new (zero total hours TIS) 

collective lever P/N 412–010–408–101 unless 

a permanent penalty of 5,000 hours TIS has 

been added to the total hours TIS on its 

component history card or equivalent record. 

(4) As of the effective date of this AD, do 

not install a used collective lever P/N 412– 

010–408–101 unless a permanent penalty of 

50% of the total hours TIS accumulated by 

the collective lever has been added to the 

total hours TIS on its component history card 

or equivalent record. 

(h) Special Flight Permits 

Special flight permits are prohibited. 

(i) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, DSCO 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 (j) of this AD. 

Information may be emailed to: 9-ASW-190- 

COS@faa.gov. 

(2) Before using any approved AMOC, 

notify your appropriate principal inspector, 

or lacking a principal inspector, the manager 

of the local flight standards district office/ 

certificate holding district office. 

(j) Related Information 

For more information about this AD, 

contact Haytham Alaidy, Aerospace 

Engineer, Certification & Program 

Management Section, DSCO Branch, 

Compliance & Airworthiness Division, FAA, 

10101 Hillwood Pkwy., Fort Worth, TX 

76177; telephone (817) 222–5224; email 

haytham.alaidy@faa.gov. 

Issued on August 19, 2021. 

Ross Landes, 

Deputy Director for Regulatory Operations, 

Compliance & Airworthiness Division, 

Aircraft Certification Service. 

[FR Doc. 2021–18383 Filed 8–26–21; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2021–0661; Project 

Identifier AD–2020–01349–E] 

RIN 2120–AA64 

Airworthiness Directives; Pratt & 

Whitney Turbofan Engines 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: The FAA proposes to 

supersede Airworthiness Directive (AD) 

2011–07–02, which applies to all Pratt 

& Whitney (P&W) JT8D–209, JT8D–217, 

JT8D–217A, JT8D–217C, and JT8D–219 

model turbofan engines. AD 2011–07– 

02 requires initial and repetitive torque 

inspections of the 3rd-stage and 4thstage low-pressure turbine (LPT) blades. 

AD 2011–07–02 also requires 

replacement of the LPT blade if wear 

limits are exceeded, replacement of the 

LPT-to-exhaust case bolts and nuts, and 

installation of crushable sleeve spacers 

on the bolts. Since the FAA issued AD 

2011–07–02, the FAA received a report 

of an MD–82 airplane, equipped with a 

JT8D–217 engine, experiencing an 

engine surge that resulted in the fracture 

of an LPT blade. This proposed AD 

would retain certain requirements of AD 

2011–07–02, while revising the 

inspection thresholds and replacement 

intervals for the 3rd-stage and 4th-stage 

LPT blades. 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 October 12, 

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 Pratt & Whitney, 

400 Main Street, East Hartford, CT 

06118; phone: (800) 565–0140; email: 

help24@prattwhitney.com; website: 

https://fleetcare.prattwhitney.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–2021–0661; 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) 238–7116; 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–2021–0661; Project Identifier AD– 

2020–01349–E’’ at the beginning of your 

comments. The most helpful comments 

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 the proposal 

because of those comments. 

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:// 


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Federal Register / Vol. 86, No. 164 / Friday, August 27, 2021 / Proposed Rules 48081 

www.regulations.gov, including any 

personal information you provide. The 

agency will also post a report 

summarizing each substantive verbal 

contact received about this proposed 

AD. 

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 

The FAA issued AD 2011–07–02, 

Amendment 39–16639 (76 FR 16526, 

March 24, 2011), (AD 2011–07–02), for 

all P&W JT8D–209, JT8D–217, JT8D– 

217A, JT8D–217C, and JT8D–219 model 

turbofan engines. AD 2011–07–02 was 

prompted by nine reports of failure of 

Tinidur material LPT-to-exhaust case 

bolts. AD 2011–07–02 requires initial 

and repetitive torque inspections of the 

3rd-stage and 4th-stage LPT blades, 

replacement of the LPT blade if wear 

limits are exceeded, and replacement of 

the LPT-to-exhaust case bolts and nuts 

with longer bolts and nuts made of 

Tinidur material. AD 2011–07–02 also 

requires installation of crushable sleeve 

spacers on the bolts. The agency issued 

AD 2011–07–02 to prevent an LPT blade 

failure that could result in uncontained 

engine debris and damage to the 

airplane. 

Actions Since AD 2011–07–02 Was 

Issued 

Since the FAA issued AD 2011–07– 

02, the agency received a report of an 

MD–82 airplane, equipped with JT8D– 

217C model turbofan engines that, on 

approach to Taipei Songshan Airport, 

experienced an engine surge on the 

number one engine resulting in LPT 

blade fracture and uncontained LPT 

blade failure. An inspection by the 

manufacturer determined that this event 

was caused by shroud notch wear of the 

LPT blades, which led to changes in the 

vibration mode and subsequent highcycle fatigue of the airfoil. In addition 

to this event, the FAA received reports 

of five events that involved uncontained 

failure of the LPT blades on the affected 

engines. Based on its investigation of 

these events, P&W determined that 

revised or more restrictive inspection 

thresholds and replacement intervals of 

the 3rd-stage and 4th-stage LPT blades 

are necessary and revised its service 

information accordingly. 

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 Pratt & Whitney 

Alert Service Bulletin (ASB) No. JT8D 

A6224, Revision No. 7, dated August 26, 

2019. This service information specifies 

procedures for the initial and repetitive 

torque inspections of the 3rd-stage and 

4th-stage LPT blades for shroud notch 

wear at revised inspection thresholds 

and intervals. 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. 

Other Related Service Information 

The FAA reviewed Pratt & Whitney 

ASB No. JT8D A6494, Revision No. 1, 

dated January 26, 2010, Pratt & Whitney 

ASB JT8D A6507, dated November 2, 

2020, and Sections 72–53–12 through 

72–53–13 of Pratt & Whitney Engine 

Maintenance Manual (EMM), Part No. 

773128, Revision 107, dated October 15, 

2020. Pratt & Whitney ASB No. JT8D 

A6494, Revision No. 1, dated January 

26, 2010, describes procedures for 

replacing the LPT-to-exhaust case bolts 

and nuts and installing the crushable 

sleeve spacers. Pratt & Whitney ASB 

JT8D A6507, dated November 2, 2020, 

describes procedures for replacing the 

3rd-stage and 4th-stage LPT blades. 

Sections 72–53–12 through 72–53–13 of 

Pratt & Whitney EMM, Part No. 773128, 

Revision 107, dated October 15, 2020, 

describe procedures for inspecting and 

repairing the 3rd-stage and 4th-stage 

LPT blades. 

Proposed AD Requirements in This 

NPRM 

This proposed AD would retain 

certain requirements of AD 2011–07–02. 

This proposed AD would require an 

initial torque inspection of certain 3rdstage LPT blades and repetitive torque 

inspections of 4th-stage LPT blades for 

shroud notch wear at revised inspection 

thresholds and intervals. This proposed 

AD would also require replacement of 

the 3rd-stage and 4th-stage LPT blades 

before accumulating 5,000 hours timein-service. 

Costs of Compliance 

The FAA estimates that this AD, if 

adopted as proposed, would affect 42 

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 

Inspect 3rd-stage and 4th-stage LPT blades ................ 1 work-hour × $85 per hour = $85 .. $0 $85 $3,570 

Replace 3rd-stage and 4th-stage LPT blades .............. 150 work-hours × $85 per hour = 

$12,750.

350,000 362,750 15,235,500 

Replace the LPT-to-exhaust case bolts and nuts and 

install the crushable sleeve spacers.

1.5 work-hours × $85 per hour = 

127.50.

4,576 4,703.50 197,547 

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. 


lotter on DSK11XQN23PROD with PROPOSALS1
48082 Federal Register / Vol. 86, No. 164 / Friday, August 27, 2021 / Proposed Rules 

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 that the 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: 

■ a. Removing Airworthiness Directive 

AD 2011–07–02, Amendment 39–16639 

(76 FR 16526, March 24, 2011); and 

■ b. Adding the following new 

airworthiness directive: 

Pratt & Whitney: Docket No. FAA–2021– 

0661; Project Identifier AD–2020–01349– 

E. 

(a) Comments Due Date 

The FAA must receive comments on this 

airworthiness directive (AD) action by 

October 12, 2021. 

(b) Affected ADs 

This AD replaces AD 2011–07–02, 

Amendment 39–16639 (76 FR 16526, March 

24, 2011). 

(c) Applicability 

This AD applies to Pratt & Whitney (P&W) 

JT8D–209, JT8D–217, JT8D–217A, JT8D– 

217C, and JT8D–219 model turbofan engines. 

(d) Subject 

Joint Aircraft System Component (JASC) 

Code 7230, Turbine Engine Compressor 

Section. 

(e) Unsafe Condition 

This AD was prompted by a report of an 

MD–82 airplane, equipped with a JT8D–217C 

model turbofan engine, experiencing an 

engine surge that resulted in the fracture of 

the low-pressure turbine (LPT) blade and 

uncontained release of the LPT blade. Five 

prior uncontained LPT blade failures were 

also reported on affected model turbofan 

engines. The FAA is issuing this AD to 

prevent LPT blade fracture and uncontained 

release of the LPT blade. The unsafe 

condition, if not addressed, could result in 

uncontained engine debris, damage to the 

engine, and damage to the aircraft. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Required Actions 

(1) For JT8D–209, JT8D–217, and JT8D– 

217A model turbofan engines, within the 

compliance times specified in the 

Accomplishment Instructions, Part 1: JT8D– 

209, –217, –217A Engines (Part 1), paragraph 

1.A., of P&W Alert Service Bulletin No. JT8D 

A6224, Revision No. 7, dated August 26, 

2019 (the ASB), perform an initial torque 

inspection for shroud notch wear of the 3rdstage LPT blades using the procedures in Part 

1, paragraph 1, of the ASB. 

(i) Thereafter, within the applicable 

reinspection interval specified in Table 1— 

Reinspection Interval for all 3rd Stage Blades, 

of the ASB, repeat the torque inspection for 

shroud notch wear required by paragraph 

(g)(1) of this AD. 

(ii) If the results of the torque inspection 

required by paragraphs (g)(1) or (g)(1)(i) of 

this AD meet the criteria for engine removal 

specified in Table 1—Reinspection Interval 

for all 3rd Stage Blades, of the ASB, perform 

piece-part inspections in accordance with the 

Instructions for Continued Airworthiness 

(ICA) on all 3rd-stage LPT blades before 

exceeding 20 hours time-in-service (TIS) 

since the last torque inspection. 

(2) For JT8D–209, JT8D–217, and JT8D– 

217A model turbofan engines, within the 

compliance times specified in Table A or 

Table B, of the ASB, as applicable, perform 

an initial torque inspection for shroud notch 

wear of the 4th-stage LPT blades using the 

procedures in Part 1, paragraph 1, of the 

ASB. Wherever the ASB refers to ‘‘Revision 

7 Release Date’’ and ‘‘At SB Release Date,’’ 

use the effective date of this AD. 

(i) For engines in which the last inspection 

prior to the effective date of this AD had a 

torque inspection result of less than 15 LB– 

IN on any 4th-stage LPT blade, perform 

piece-part inspections in accordance with the 

ICA on all 3rd-stage and 4th-stage LPT blades 

within 20 hours TIS after the effective date 

of this AD. 

(ii) Thereafter, within the applicable 

reinspection interval specified in Table 2— 

Reinspection Interval for all 4th Stage Blades, 

of the ASB, repeat the torque inspection for 

shroud notch wear required by paragraph 

(g)(2) of this AD. 

(iii) If the results of the torque inspection 

required by paragraphs (g)(2) or (g)(2)(ii) of 

this AD meet the criteria for engine removal 

specified in Table 2—Reinspection Interval 

for all 4th Stage Blades, of the ASB, perform 

piece-part inspections in accordance with the 

ICA on all 3rd-stage and 4th-stage LPT blades 

before exceeding 20 hours TIS since the last 

torque inspection. 

(3) For JT8D–217C and JT8D–219 model 

turbofan engines, within the compliance 

times specified in Table A or Table B, of the 

ASB, as applicable, perform an initial torque 

inspection for shroud notch wear of the 4thstage LPT blades using the procedures in the 

Accomplishment Instructions, Part 2: JT8D– 

217C, –219 Engines (Part 2), paragraph 1, of 

the ASB. Wherever the ASB refers to 

‘‘Revision 7 Release Date’’ and ‘‘At SB 

Release Date,’’ use the effective date of this 

AD. 

(i) For engines in which the last inspection 

prior to the effective date of this AD had a 

torque inspection result of less than 15 LB– 

IN on any 4th-stage LPT blade, perform 

piece-part inspections in accordance with the 

ICA on all 3rd-stage and 4th-stage LPT blades 

within 20 hours TIS after the effective date 

of this AD. 

(ii) Thereafter, within the reinspection 

interval specified in Table 3-Reinspection 

Interval for all 4th Stage Blades, of the ASB, 

repeat the torque inspection for shroud notch 

wear required by paragraph (g)(3) of this AD. 

(iii) If the results of the torque inspection 

required by paragraph (g)(3) and (g)(3)(ii) of 

this AD meet the criteria for engine removal 

specified in Table 3—Reinspection Interval 

for all 4th Stage Blades, of the ASB, perform 

piece-part inspections in accordance with the 

ICA on all 3rd-stage and 4th-stage LPT blades 

before exceeding 20 hours TIS since the last 

torque inspection. 

(4) At the first engine shop visit after 

January 1, 2023, or prior to accumulating 

5,000 TIS on the 3rd-stage and 4th-stage LPT 

blades, whichever occurs later, but not to 

exceed 6 years after the effective date of the 

AD, replace the 3rd-stage and 4th-stage LPT 

blades with parts eligible for installation. 

(5) Thereafter, prior to accumulating 5,000 

hours TIS on the 3rd-stage and 4th-stage LPT 

blades since their last replacement, replace 

the 3rd-stage and 4th-stage LPT blades with 

parts eligible for installation. 

(6) After every replacement of the 3rd-stage 

or 4th-stage LPT blades, perform initial and 

repetitive torque inspections of the 3rd-stage 

or 4th-stage LPT blades using, as applicable, 

the accomplishment instructions and 


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compliance times in Part 1, paragraph 1, or 

Part 2, paragraph 1, of the ASB. 

(i) If the results of the torque inspection 

required by paragraph (g)(6) of this AD meet 

the criteria for engine removal specified in 

Table 1, 2 or 3, of the ASB, as applicable, 

perform piece-part inspections in accordance 

with the ICA on all 3rd-stage and 4th-stage 

LPT blades before exceeding 20 hours TIS 

since the last torque inspection. 

(ii) [Reserved] 

(7) The initial inspection or the 

reinspection interval should not be reset 

unless the blades are refurbished. Whenever 

a used blade is reinstalled in a rotor, the 

previous used time should be subtracted 

from the initial inspection threshold. 

(8) Whenever a refurbished or used blade 

is intermixed with zero hours time-since-new 

(TSN) blades in a rotor, use the lowest initial 

inspection threshold that is applicable. 

(9) At the next accessibility to the LPT-toexhaust case bolts and nuts after the effective 

date of this AD, do the following: 

(i) Replace the bolts with part number (P/ 

N) MS9557–26 bolts; 

(ii) Replace the nuts with P/N 375095 nuts 

or P/N 490270 nuts; and 

(iii) Install crushable sleeve spacers, P/N 

822903, under the head of the bolts. 

Note 1 to paragraph (g): Guidance on 

replacing the 3rd-stage and 4th-stage LPT 

blades can be found in P&W ASB JT8D 

A6507, dated November 2, 2020. 

Note 2 to paragraph (g): Guidance on 

replacing the LPT-to-exhaust case bolts and 

nuts and installing the crushable sleeve 

spacers can be found in P&W ASB No. JT8D 

A6494, Revision No. 1, dated January 26, 

2010. 

(h) Definitions 

For the purpose of this AD: 

(1) 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, except that the 

separation of engine flanges solely for the 

purposes of transportation without 

subsequent engine maintenance does not 

constitute an engine shop visit. 

(2) Accessibility to the LPT-to-exhaust case 

bolts refers to maintenance involving the 

inner turbine fan ducts being removed from 

the engine. 

(3) Parts eligible for installation are 3rdstage or 4th-stage LPT blades with less than 

5,000 hours TIS. 

(4) A ‘‘piece-part inspection’’ is when the 

blades are removed from the rotor. 

(5) A ‘‘used blade’’ refers to a 3rd-stage or 

4th-stage LPT blade that has more than zero 

hours TSN. 

(i) Credit for Previous Actions 

You may take credit for any initial torque 

inspection for shroud notch wear required by 

paragraphs (g)(1) through (3) of this AD if you 

performed the initial inspection before the 

effective date of this AD using P&W ASB No. 

JT8D A6224, Revision No. 5, dated June 11, 

2004, or Revision No. 6, dated May 3, 2007. 

(j) 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 ECO Branch, 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. 

(k) 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) 

238–7116; fax: (781) 238–7199; email: 

nicholas.j.paine@faa.gov. 

(2) For service information identified in 

this AD, contact Pratt & Whitney, 400 Main 

Street, East Hartford, CT 06118; phone: (800) 

565–0140; email: help24@prattwhitney.com; 

website: https://fleetcare.prattwhitney.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 August 5, 2021. 

Lance T. Gant, 

Director, Compliance & Airworthiness 

Division, Aircraft Certification Service. 

[FR Doc. 2021–18489 Filed 8–26–21; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2021–0712; Project 

Identifier 2019–CE–018–AD] 

RIN 2120–AA64 

Airworthiness Directives; ASI Aviation 

(Type Certificate Previously Held by 

Reims Aviation S.A.) Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: The FAA proposes to 

supersede Airworthiness Directive (AD) 

2015–16–07 R1, which applies to 

certain Reims Aviation S.A. (type 

certificate now held by ASI Aviation) 

Model F406 airplanes. AD 2015–16–07 

R1 requires inspecting the left-hand and 

right-hand rudder control pedal torque 

tubes and replacing with a serviceable 

part as necessary. Since the FAA issued 

AD 2015–16–07 R1, the European 

Aviation Safety Agency (EASA) 

superseded its mandatory continuing 

airworthiness information (MCAI) to 

correct an unsafe condition on these 

products. This proposed AD would 

retain the requirements of AD 2015–16– 

07 R1, expand the applicability, and 

require repeating the inspections using 

updated procedures. 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 October 12, 

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 ASI Aviation, 

Ae ́rodrome de Reims Prunay, 51360 

Prunay, France; telephone: +33 3 26 48 

46 84; fax: +33 3 26 49 18 57; email: 

contact@asi-aviation.fr; website: https:// 

asi-aviation.fr/page-Accueil.html. 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 (816) 329– 

4148. 

Examining the AD Docket 

You may examine the AD docket at 

https://www.regulations.gov by 

searching for and locating Docket No. 

FAA–2021–0712; 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, the MCAI, any comments 

received, and other information. The 

street address for Docket Operations is 

listed above. 

FOR FURTHER INFORMATION CONTACT: 

Gregory Johnson, Aviation Safety 

Engineer, FAA, General Aviation & 

Rotorcraft Section, International 

Validation Branch, 901 Locust, Room 

301, Kansas City, MO 64106; phone: 

(720) 626–5462; fax: (816) 329–4090; 

email: gregory.johnson@faa.gov. 

SUPPLEMENTARY INFORMATION: 


lotter on DSK11XQN23PROD with PROPOSALS1