Federal Register / Vol. 86, No. 157 / Wednesday, August 18, 2021 / Rules and Regulations 46111 

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: 

2021–16–14 BALO ́ NY KUBI ́Cˇ EK spol. s r.o.: 

Amendment 39–21676; Docket No. 

FAA–2021–0618; Project Identifier 

2019–CE–005–AD. 

(a) Effective Date 

This airworthiness directive (AD) is 

effective September 7, 2021. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to the following BALO ́ NY 

KUBI ́Cˇ EK spol. s r.o. balloons, certificated in 

any category: 

(1) Model BB78Z, serial numbers (S/Ns) 

1292 and 1364; 

(2) Model BB85Z, S/N 1360; 

(3) Model BB92Z, S/N 1331; and 

(4) Model BB130P, S/N 1397. 

(d) Subject 

Joint Aircraft System Component (JASC) 

Code 5300, Fuselage. 

(e) Unsafe Condition 

This AD was prompted by mandatory 

continuing airworthiness information (MCAI) 

issued by the aviation authority of another 

country to identify and correct an unsafe 

condition on an aviation product. The MCAI 

describes the unsafe condition as failure of 

the envelope vertical load tape. The FAA is 

issuing this AD to detect and correct defects 

in the envelope vertical load tape, which 

could result in an envelope tear and 

consequent uncontrolled descent. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Inspection and Repair 

Within 30 days after the effective date of 

this AD, inspect the envelope load tape for 

weaving defects indicated by visible yellow 

thread. If there is visible yellow thread in any 

envelope load tape, before further flight, 

repair any damaged area of the envelope load 

tape. 

Note 1 to paragraph (g): BALO ́ NY 

KUBI ́Cˇ EK spol. s r.o. Servis Bulletin No. BB/ 

52, dated July 23, 2018, includes an example 

of a weaving defect and specifies acceptable 

procedures and materials for repairing 

envelope load tape. 

(h) 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 Related Information, paragraph 

(i)(1) of this AD or email 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. 

(i) Related Information 

(1) For more information about this AD, 

contact Mike Kiesov, Aviation Safety 

Engineer, General Aviation & Rotorcraft 

Section, International Validation Branch, 

FAA, 901 Locust, Room 301, Kansas City, 

MO 64106; phone: (816) 329–4144; fax: (816) 

329–4090; email: mike.kiesov@faa.gov. 

(2) Refer to European Aviation Safety 

Agency (EASA) AD 2018–0181, dated August 

27, 2018, for more information. You may 

examine the EASA AD in the AD docket at 

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

and locating it in Docket No. 

(j) Material Incorporated by Reference 

None. 

Issued on August 5, 2021. 

Lance T. Gant, 

Director, Compliance & Airworthiness 

Division, Aircraft Certification Service. 

[FR Doc. 2021–17604 Filed 8–17–21; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2021–0447; Project 

Identifier AD–2021–00131–E; Amendment 

39–21692; AD 2021–17–09] 

RIN 2120–AA64 

Airworthiness Directives; Pratt & 

Whitney Turbofan Engines 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: The FAA is adopting a new 

airworthiness directive (AD) for all Pratt 

& Whitney PW1500G and PW1900G 

series turbofan engines. This AD was 

prompted by reports of cracks in the 

high-pressure compressor (HPC) rotor 

shaft that resulted in in-flight 

shutdowns (IFSDs) and unscheduled 

engine removals (UERs). This AD 

requires removal and replacement of the 

HPC front hub and HPC rotor shaft. The 

FAA is issuing this AD to address the 

unsafe condition on these products. 

DATES: This AD is effective September 

22, 2021. 

ADDRESSES: For service information 

identified in this final rule, contact Pratt 

& Whitney, 400 Main Street, East 

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

0140; email: help24@pw.utc.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. It is also available at https://

www.regulations.gov by searching for 

and locating Docket No. FAA–2021– 

0447. 

Examining the AD Docket 

You may examine the AD docket at 

https://www.regulations.gov by 

searching for and locating Docket No. 

FAA–2021–0447; or in person at Docket 

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

Monday through Friday, except Federal 

holidays. The AD docket contains this 

final rule, any comments received, and 

other information. The address for 

Docket Operations is U.S. Department of 

Transportation, Docket Operations, M– 

30, West Building Ground Floor, Room 

W12–140, 1200 New Jersey Avenue SE, 

Washington, DC 20590. 

FOR FURTHER INFORMATION CONTACT: 

Mark Taylor, Aviation Safety Engineer, 

ECO Branch, FAA, 1200 District 

Avenue, Burlington, MA 01803; phone: 

(781) 238–7229; fax: (781) 238–7199; 

email: Mark.Taylor@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 all PW1519G, PW1521G, 

PW1521G–3, PW1521GA, PW1524G, 

PW1524G–3, PW1525G, PW1525G–3, 

PW1919G, PW1921G, PW1922G, 

PW1923G, and PW1923G–A model 

turbofan engines. The NPRM published 

in the Federal Register on June 3, 2021 

(86 FR 29707). The NPRM was 

prompted by reports of cracks in the 

HPC rotor shaft that resulted in 

vibration and subsequent IFSDs and 


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46112 Federal Register / Vol. 86, No. 157 / Wednesday, August 18, 2021 / Rules and Regulations 

UERs. The manufacturer determined 

that the threads on the HPC rotor shaft 

were not optimized for load 

distribution, which resulted in vibration 

stresses. During one occurrence, oil was 

released at the high-pressure turbine 

(HPT) disk bore location. The 

manufacturer redesigned the HPC front 

hub and HPC rotor shaft for increased 

durability and decreased vibration 

stress. The redesigned HPC front hub is 

made from nickel to help with corrosion 

resistance. The threads on the HPC rotor 

shaft were also redesigned to help 

distribute the load on the threads and 

decrease vibration stress. In the NPRM, 

the FAA proposed to require removal 

and replacement of the HPC front hub 

and HPC rotor shaft. 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 

one commenter, the Air Line Pilots 

Association, International (ALPA). 

ALPA supported the NPRM without 

change. 

Conclusion 

The FAA reviewed the relevant data, 

considered the comments received, and 

determined that air safety requires 

adopting the AD as proposed. 

Accordingly, the FAA is issuing this AD 

to address the unsafe condition on these 

products. This AD is adopted as 

proposed in the NPRM. 

Related Service Information 

The FAA reviewed Pratt & Whitney 

Service Bulletin (SB) PW1000G–A–72– 

00–0154–00A–930A–D, Issue No. 001, 

dated May 7, 2021 (PW1000G–A–72– 

00–0154–00A–930A–D), and Pratt & 

Whitney SB PW1000G–A–72–00–0101– 

00B–930A–D, Issue No. 001, dated May 

7, 2021 (SB PW1000G–A–72–00–0101– 

00B–930A–D). These SBs describe 

procedures for removing and replacing 

the HPC front hub and HPC rotor shaft. 

Costs of Compliance 

The FAA estimates that this AD 

affects 88 engines installed on 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 

Replace HPC front hub and HPC rotor shaft 25.75 work-hours × $85 per hour = 

$2,188.75.

$120,090 $122,278.75 $10,760,530 

Authority for This Rulemaking 

Title 49 of the United States Code 

specifies the FAA’s authority to issue 

rules on aviation safety. Subtitle I, 

section 106, describes the authority of 

the FAA Administrator. Subtitle VII: 

Aviation Programs, describes in more 

detail the scope of the Agency’s 

authority. 

The FAA is issuing this rulemaking 

under the authority described in 

Subtitle VII, Part A, Subpart III, Section 

44701: General requirements. Under 

that section, Congress charges the FAA 

with promoting safe flight of civil 

aircraft in air commerce by prescribing 

regulations for practices, methods, and 

procedures the Administrator finds 

necessary for safety in air commerce. 

This regulation is within the scope of 

that authority because it addresses an 

unsafe condition that is likely to exist or 

develop on products identified in this 

rulemaking action. 

Regulatory Findings 

This AD will not have federalism 

implications under Executive Order 

13132. This AD will not have a 

substantial direct effect on the States, on 

the relationship between the national 

government and the States, or on the 

distribution of power and 

responsibilities among the various 

levels of government. 

For the reasons discussed above, I 

certify that this AD: 

(1) Is not a ‘‘significant regulatory 

action’’ under Executive Order 12866, 

(2) Will not affect intrastate aviation 

in Alaska, and 

(3) Will not have a significant 

economic impact, positive or negative, 

on a substantial number of small entities 

under the criteria of the Regulatory 

Flexibility Act. 

List of Subjects in 14 CFR Part 39 

Air transportation, Aircraft, Aviation 

safety, Incorporation by reference, 

Safety. 

The Amendment 

Accordingly, under the authority 

delegated to me by the Administrator, 

the FAA amends 14 CFR part 39 as 

follows: 

PART 39—AIRWORTHINESS 

DIRECTIVES 

■ 1. The authority citation for part 39 

continues to read as follows: 

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

§ 39.13 [Amended] 

■ 2. The FAA amends § 39.13 by adding 

the following new airworthiness 

directive: 

2021–17–09 Pratt & Whitney: Amendment 

39–21692; Docket No. FAA–2021–0447; 

Project Identifier AD–2021–00131–E. 

(a) Effective Date 

This airworthiness directive (AD) is 

effective September 22, 2021. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to Pratt & Whitney 

PW1519G, PW1521G, PW1521G–3, 

PW1521GA, PW1524G, PW1524G–3, 

PW1525G, PW1525G–3, PW1919G, 

PW1921G, PW1922G, PW1923G, and 

PW1923G–A model turbofan engines. 

(d) Subject 

Joint Aircraft System Component (JASC) 

Code 7230, Turbine Engine Compressor 

Section. 

(e) Unsafe Condition 

This AD was prompted by reports of cracks 

in the high-pressure compressor (HPC) rotor 

shaft that resulted in in-flight shutdowns and 

unscheduled engine removals. The FAA is 

issuing this AD to prevent cracking of the 

HPC rotor shaft. The unsafe condition, if not 

addressed, could result in release of a highpressure turbine disk, damage to the engine, 

and damage to the airplane. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Required Action 

At the next engine shop visit after the 

effective date of this AD, remove HPC front 

hub, part number (P/N) 30G1910 or 30G3210, 

and HPC rotor shaft, P/N 30G1854, 30G3109, 

30G4995, 30G4953, or 31G0014, from service 

and replace each part with a part eligible for 

installation. 


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Federal Register / Vol. 86, No. 157 / Wednesday, August 18, 2021 / Rules and Regulations 46113 

(h) Definitions 

(1) 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 

case flanges, except for the following, which 

do not constitute an engine shop visit: 

(i) Separation of engine flanges solely for 

the purposes of transportation without 

subsequent maintenance does not constitute 

an engine shop visit. 

(ii) Separation of engine flanges solely for 

the purpose of replacing the fan without 

subsequent maintenance does not constitute 

an engine shop visit. 

(2) For the purpose of this AD, a ‘‘part 

eligible for installation’’ is: 

(i) For an HPC front hub: any HPC front 

hub with a P/N other than P/N 30G1910 or 

30G3210; and 

(ii) For an HPC rotor shaft: any HPC rotor 

shaft with a P/N other than P/N 30G1854, 

30G3109, 30G4995, 30G4953, or 31G0014. 

(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 

For more information about this AD, 

contact Mark Taylor, Aviation Safety 

Engineer, ECO Branch, FAA, 1200 District 

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

238–7229; fax: (781) 238–7199; email: 

Mark.Taylor@faa.gov. 

(k) Material Incorporated by Reference 

None. 

Issued on August 12, 2021. 

Lance T. Gant, 

Director, Compliance & Airworthiness 

Division, Aircraft Certification Service. 

[FR Doc. 2021–17654 Filed 8–17–21; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2021–0364; Project 

Identifier MCAI–2020–00274–R; Amendment 

39–21675; AD 2021–16–13] 

RIN 2120–AA64 

Airworthiness Directives; Leonardo 

S.p.a. Helicopters 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: The FAA is adopting a new 

airworthiness directive (AD) for 

Leonardo S.p.a. (Leonardo) Model 

A109S and AW109SP helicopters with a 

certain part-numbered vertical fin 

vibration absorber installation installed. 

This AD requires repetitive inspections 

of the vertical fin vibration absorber 

installation and the surrounding 

structure and depending on the 

inspection results, removing certain 

parts from service. This AD also 

prohibits installing certain partnumbered vertical fin vibration absorber 

installations on any helicopter. This AD 

was prompted by a report of cracks and 

damage detected on the vertical fin 

absorber installation and surrounding 

structure during scheduled inspections. 

The FAA is issuing this AD to address 

the unsafe condition on these products. 

DATES: This AD is effective September 

22, 2021. 

ADDRESSES: For service information 

identified in this final rule, contact 

Leonardo S.p.a. Helicopters, Emanuele 

Bufano, Head of Airworthiness, Viale 

G.Agusta 520, 21017 C. Costa di 

Samarate (Va) Italy; telephone +39– 

0331–225074; fax +39–0331–229046; or 

at https://www.leonardocompany.com/ 

en/home. You may view the referenced 

service information at the FAA, Office 

of the Regional Counsel, Southwest 

Region, 10101 Hillwood Pkwy., Room 

6N–321, Fort Worth, TX 76177. 

Examining the AD Docket 

You may examine the AD docket at 

https://www.regulations.gov by 

searching for and locating Docket No. 

FAA–2021–0364; or in person at Docket 

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

Monday through Friday, except Federal 

holidays. The AD docket contains this 

final rule, the European Union Aviation 

Safety Agency (EASA) AD, any 

comments received, and other 

information. The 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: 

Kristin Bradley, Aerospace Engineer, 

General Aviation & Rotorcraft Section, 

International Validation Branch, FAA, 

10101 Hillwood Pkwy., Fort Worth, TX 

76177; telephone (817) 222–5110; email 

kristin.bradley@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 Leonardo Model A109S and 

AW109SP helicopters with a vertical fin 

vibration absorber installation part 

number (P/N) 109–B810–79–101 

installed. The NPRM published in the 

Federal Register on May 13, 2021 (86 

FR 26198). In the NPRM, the FAA 

proposed, within 30 hours time-inservice (TIS), and thereafter at intervals 

not to exceed 100 hours TIS, removing 

the vertical fin vibration absorber 

installation and, using a mirror and light 

source, inspecting the rib assembly and 

depending on the inspection results, 

removing certain parts from service. The 

NPRM also proposed to require 

inspecting the vertical fin vibration 

absorber installation for hole elongation; 

for fretting between the plate and the 

masses, and in between the masses; for 

fretting on the doubler; and the bolts for 

scratches and corrosion. Depending on 

the inspection results, the NPRM 

proposed removing the vertical fin 

vibration absorber installation from 

service. The NPRM also proposed to 

require, within 12 months TIS, 

removing the vertical fin vibration 

absorber installation from service. 

Finally, the NPRM proposed to prohibit 

installing an affected part on any 

helicopter, and provided a terminating 

action for the 100-hour TIS repetitive 

inspections. 

The NPRM was prompted by EASA 

AD 2014–0150, dated June 18, 2014 

(EASA AD 2014–0150), issued by 

EASA, which is the Technical Agent for 

the Member States of the European 

Union, to correct an unsafe condition 

for certain AgustaWestland S.p.A. (now 

Leonardo S.p.a. Helicopters) (formerly 

Agusta S.p.A.) Model A109S and 

AW109SP helicopters with an absorber 

P/N 109–B810–79–101installed. EASA 

advises that during a scheduled 

inspection on Model A109S and 

AW109SP helicopters, cracks and 

damage were detected on the vertical fin 

vibration absorber installation and the 

surrounding structure. EASA stated that 

investigation results determined the 


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