40158 Federal Register / Vol. 81, No. 119 / Tuesday, June 21, 2016 / Rules and Regulations 

U.S. Code citation CMP Description New maximum amount 

(3) 12 U.S.C. 1782(a)(3) .................................... Failure to submit a report or the submission of 

a false or misleading report done knowingly 

or with reckless disregard.

1,893,610 or 1 percent of the total assets of 

the credit union, whichever is less. 

(4) 12 U.S.C. 1782(d)(2)(A) ................................ Tier 1 CMP for inadvertent failure to submit 

certified statement of insured shares and 

charges due to NCUSIF, or inadvertent 

submission of false or misleading statement.

3,462. 

(5) 12 U.S.C. 1782(d)(2)(B) ................................ Tier 2 CMP for non-inadvertent failure to submit certified statement or submission of 

false or misleading statement.

34,620. 

(6) 12 U.S.C. 1782(d)(2)(C) ............................... Tier 3 CMP for failure to submit a certified 

statement or the submission of a false or 

misleading statement done knowingly or 

with reckless disregard.

1,730,990 or 1 percent of the total assets of 

the credit union, whichever is less. 

(7) 12 U.S.C. 1785(a)(3) .................................... Non-compliance with insurance logo requirements.118. 

(8) 12 U.S.C. 1785(e) (3) ................................... Non-compliance with NCUA security requirements.275. 

(9) 12 U.S.C. 1786(k)(2)(A) ................................ Tier 1 CMP for violations of law, regulation, 

and other orders or agreements.

9,468. 

(10) 12 U.S.C. 1786(k)(2)(A) .............................. Tier 2 CMP for violations of law, regulation, 

and other orders or agreements and for 

recklessly engaging in unsafe or unsound 

practices or breaches of fiduciary duty.

47,340. 

(11) 12 U.S.C. 1786(k)(2)(A) .............................. Tier 3 CMP for knowingly committing the violations under Tier 1 or 2 (natural person).For a person other than an insured credit 

union: $1,893,610; 

For an insured credit union: $1,893,610 or 1 

percent of the total assets of the credit 

union, whichever is less. 

(12) 12 U.S.C. 1786(w)(5)(ii) .............................. Non-compliance with senior examiner postemployment restrictions.311,470. 

(13) 15 U.S.C. 1639e(k) ..................................... Non-compliance with appraisal independence 

requirements.

First violation: $10,875 

Subsequent violations: $21,749. 

(14) 42 U.S.C. 4012a(f)(5) ................................. Non-compliance with flood insurance requirements.2,056. 

(b) The adjusted amounts displayed in 

paragraph (a) of this section apply to 

civil monetary penalties that are 

assessed after the date the increase takes 

effect, including those whose associated 

violation or violations predate the 

increase. 

[FR Doc. 2016–14719 Filed 6–20–16; 8:45 am] 

BILLING CODE 7535–01–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2010–0219; Directorate 

Identifier 2010–NE–14–AD; Amendment 39– 

18556; AD 2016–12–07] 

RIN 2120–AA64 

Airworthiness Directives; Turbomeca 

S.A. Turboshaft Engines 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are superseding 

airworthiness directive (AD) 2010–11– 

10 for all Turbomeca S.A. Astazou XIV 

B and XIV H turboshaft engines. AD 

2010–11–10 requires inspection of 

certain third stage turbine wheels and 

removal of any damaged wheel. This AD 

requires expanding the population and 

frequency of repetitive inspections. This 

AD was prompted by a report of a third 

stage turbine wheel crack detected 

during engine overhaul. We are issuing 

this AD to prevent uncontained failure 

of the third stage turbine wheel, which 

could result in damage to the engine 

and damage to the helicopter. 

DATES: This AD is effective July 26, 

2016. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in this AD 

as of July 26, 2016. 

ADDRESSES: For service information 

identified in this final rule, contact 

Turbomeca S.A., 40220 Tarnos, France; 

phone: (33) 05 59 74 40 00; fax: (33) 05 

59 74 45 15. You may view this service 

information at the FAA, Engine & 

Propeller Directorate, 1200 District 

Avenue, Burlington, MA. For 

information on the availability of this 

material at the FAA, call 781–238–7125. 

It is also available on the Internet at 

http://www.regulations.gov by searching 

for and locating Docket No. FAA–2010– 

0219. 

Examining the AD Docket 

You may examine the AD docket on 

the Internet at http://

www.regulations.gov by searching for 

and locating Docket No. FAA–2010– 

0219; or in person at the Docket 

Management Facility between 9 a.m. 

and 5 p.m., Monday through Friday, 

except Federal holidays. The AD docket 

contains this AD, the mandatory 

continuing airworthiness information, 

regulatory evaluation, any comments 

received, and other information. The 

address for the Docket Office (phone: 

800–647–5527) is Document 

Management Facility, 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: 

Brian Kierstead, Aerospace Engineer, 

Engine Certification Office, FAA, Engine 

& Propeller Directorate, 1200 District 

Avenue, Burlington, MA 01803; phone: 

781–238–7772, fax: 781–238–7199; 

email: brian.kierstead@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 


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Federal Register / Vol. 81, No. 119 / Tuesday, June 21, 2016 / Rules and Regulations 40159 

part 39 to supersede AD 2010–11–10, 

Amendment 39–16315 (75 FR 30270, 

June 1, 2010), (‘‘AD 2010–11–10’’). AD 

2010–11–10 applied to the specified 

products. The NPRM published in the 

Federal Register on March 11, 2016 (81 

FR 12843) (‘‘the NPRM’’). The NPRM 

proposed to continue to require 

inspection of certain third stage turbine 

wheels and removal of any damaged 

wheel. The NPRM also proposed to 

expand the population and frequency of 

repetitive inspections. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. We 

received no comments on the NPRM. 

Conclusion 

We reviewed the available data and 

determined that air safety and the 

public interest require adopting this AD 

as proposed. 

Related Service Information Under 1 

CFR Part 51 

Turbomeca S.A. has issued 

Mandatory Service Bulletin (MSB) No. 

283 72 0804, Version D, dated July 24, 

2015. The MSB describes procedures for 

inspecting the third stage turbine 

wheels. 

Turbomeca S.A. has issued Service 

Bulletin (SB) No. 283 72 0805, Version 

B, dated December 15, 2010. That SB 

describes optional terminating action for 

the inspections. 

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 

We estimate that this AD affects seven 

engines installed on helicopters of U.S. 

registry. We also estimate that it would 

take about 5 hours per engine to comply 

with this AD. The average labor rate is 

$85 per hour. Based on these figures, we 

estimate the cost of this AD on U.S. 

operators to be $2,975. 

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. 

We are 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) Is not a ‘‘significant rule’’ under 

DOT Regulatory Policies and Procedures 

(44 FR 11034, February 26, 1979), 

(3) Will not affect intrastate aviation 

in Alaska to the extent that it justifies 

making a regulatory distinction, and 

(4) 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. 

Adoption of the Amendment 

Accordingly, under the authority 

delegated to me by the Administrator, 

the FAA amends part 39 of the Federal 

Aviation Regulations (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 

removing airworthiness directive (AD) 

2010–11–10, Amendment 39–16315 (75 

FR 30270, June 1, 2010), (‘‘AD 2010–11– 

10’’), and adding the following new AD: 

2016–12–07 Turbomeca S.A.: Amendment 

39–18556; Docket No. FAA–2010–0219; 

Directorate Identifier 2010–NE–14–AD. 

(a) Effective Date 

This AD is effective July 26, 2016. 

(b) Affected ADs 

This AD supersedes AD 2010–11–10. 

(c) Applicability 

This AD applies to Turbomeca S.A., 

Astazou XIV B and XIV H turboshaft engines 

with the following part number (P/N) and 

serial number (S/N) third stage turbine 

wheels that incorporate modification AB 173 

(Turbomeca S.A. Service Bulletin (SB) No. 

283 72 0091) or modification AB 208 

(Turbomeca S.A. SB No. 283 72 0117). This 

AD does not apply to third stage turbine 

wheels that incorporate Turbomeca S.A. SB 

No. 283 72 805. 

(1) Third stage turbine wheels, P/N 0 265 

25 700 0, all S/Ns; 

(2) Third stage turbine wheels, P/N 0 265 

25 702 0, all S/Ns; 

(3) Third stage turbine wheels, P/N 0 265 

25 706 0, all S/Ns; 

(4) Third stage turbine wheels, P/N 0 265 

25 705 0, with an S/N listed in Appendix 2.1 

of Turbomeca S.A. Mandatory Service 

Bulletin (MSB) No. 283 72 0804, Version D, 

dated July 24, 2015. 

(d) Unsafe Condition 

This AD was prompted by a report of a 

third stage turbine wheel crack detected 

during engine overhaul. We are issuing this 

AD to prevent uncontained failure of the 

third stage turbine wheel, which could result 

in damage to the engine and damage to the 

helicopter. 

(e) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(1) Perform a dye penetrant inspection of 

the third stage turbine wheel. Use paragraph 

2.4.2.2 of Turbomeca S.A. MSB No. 283 72 

0804, Version D, dated July 24, 2015, to do 

the inspection, as follows: 

(i) Inspect third stage turbine wheels with 

300 engine cycles (EC) or more accumulated 

since last inspection, or since new, or since 

last overhaul, or since repair, within 100 EC 

after the effective date of this AD. 

(ii) Inspect third stage turbine wheels with 

less than 300 EC accumulated since last 

inspection, or since new, or since last 

overhaul, or since repair, within 400 EC since 

last inspection, or since new, or since last 

overhaul, or since repair. 

(2) Repeat the inspection required by this 

AD within 400 EC since last inspection. 

(3) Remove from service any third stage 

turbine wheels that fail the inspection 

required by this AD. 

(f) Optional Terminating Action 

Application of Turbomeca S.A. SB No. 283 

72 0805, Version B, dated December 15, 2010 

is terminating action for the inspections 

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

AD. 

(g) Alternative Methods of Compliance 

(AMOCs) 

The Manager, Engine Certification Office, 

may approve AMOCs for this AD. Use the 

procedures found in 14 CFR 39.19 to make 

your request. You may email your request to: 

ANE-AD-AMOC@faa.gov. 

(h) Related Information 

(1) For more information about this AD, 

contact Brian Kierstead, Aerospace Engineer, 


rmajette on DSK2TPTVN1PROD with RULES
40160 Federal Register / Vol. 81, No. 119 / Tuesday, June 21, 2016 / Rules and Regulations 

Engine Certification Office, FAA, Engine & 

Propeller Directorate, 1200 District Avenue, 

Burlington, MA 01803; phone: 781–238– 

7772; fax: 781–238–7199; email: 

brian.kierstead@faa.gov. 

(2) Refer to MCAI EASA AD 2015–0211, 

dated October 15, 2015, for related 

information. You may examine the MCAI in 

the AD docket on the Internet at http://

www.regulations.gov by searching for and 

locating it in Docket No. FAA–2010–0219. 

(i) Material Incorporated by Reference 

(1) The Director of the Federal Register 

approved the incorporation by reference 

(IBR) of the service information listed in this 

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

part 51. 

(2) You must use this service information 

as applicable to do the actions required by 

this AD, unless the AD specifies otherwise. 

(i) Turbomeca S.A. Mandatory Service 

Bulletin No. 283 72 0804, Version D, dated 

July 24, 2015. 

(ii) Turbomeca S.A. Service Bulletin No. 

283 72 0805, Version B, dated December 15, 

2010. 

(3) For Turbomeca S.A. service information 

identified in this AD, contact Turbomeca 

S.A., 40220 Tarnos, France; phone: (33) 05 59 

74 40 00; fax: (33) 05 59 74 45 15. 

(4) You may view this service information 

at FAA, Engine & Propeller Directorate, 1200 

District Avenue, Burlington, MA. For 

information on the availability of this 

material at the FAA, call 781–238–7125. 

(5) You may view this service information 

at the National Archives and Records 

Administration (NARA). For information on 

the availability of this material at NARA, call 

202–741–6030, or go to: http://

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

Issued in Burlington, Massachusetts, on 

June 7, 2016. 

Colleen M. D’Alessandro, 

Manager, Engine & Propeller Directorate, 

Aircraft Certification Service. 

[FR Doc. 2016–14406 Filed 6–20–16; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2016–7263; Directorate 

Identifier 2016–NM–072–AD; Amendment 

39–18564; AD 2016–12–15] 

RIN 2120–AA64 

Airworthiness Directives; Airbus 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule; request for 

comments. 

SUMMARY: We are superseding 

Airworthiness Directive (AD) 2016–07– 

30 for all Airbus Model A330–200, –200 

Freighter, and –300 series airplanes, and 

all Airbus Model A340–200, –300, –500, 

and –600 series airplanes. For certain 

airplanes, AD 2016–07–30 required 

replacing certain Angle of Attack (AOA) 

sensors (probes) with certain new AOA 

sensors. For certain other airplanes, AD 

2016–07–30 also required inspections 

and functional heat testing of certain 

AOA sensors for discrepancies, and 

replacement if necessary. This new AD 

requires the same actions as AD 2016– 

07–30. This new AD was prompted by 

a report of a typographical error in the 

regulatory text of AD 2016–07–30. We 

are issuing this AD to prevent erroneous 

AOA information and Alpha Protection 

(Alpha Prot) activation due to blocked 

AOA probes, which could result in a 

continuous nose-down command and 

consequent loss of control of the 

airplane. 

DATES: This AD is effective July 6, 2016. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in this AD 

as of May 18, 2016 (81 FR 21722, April 

13, 2016). 

We must receive comments on this 

AD by August 5, 2016. 

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 

http://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: U.S. Department of 

Transportation, Docket Operations, 

M–30, West Building Ground Floor, 

Room W12–140, 1200 New Jersey 

Avenue SE., Washington, DC, between 9 

a.m. and 5 p.m., Monday through 

Friday, except Federal holidays. 

For service information identified in 

this final rule, contact Airbus SAS, 

Airworthiness Office—EAL, 1 Rond 

Point Maurice Bellonte, 31707 Blagnac 

Cedex, France; telephone +33 5 61 93 36 

96; fax +33 5 61 93 45 80; email 

airworthiness.A330-A340@airbus.com; 

Internet http://www.airbus.com. You 

may view this referenced service 

information at the FAA, Transport 

Airplane Directorate, 1601 Lind Avenue 

SW., Renton, WA. For information on 

the availability of this material at the 

FAA, call 425–227–1221. It is also 

available on the Internet at http://

www.regulations.gov by searching for 

and locating Docket No. FAA–2016– 

7263. 

Examining the AD Docket 

You may examine the AD docket on 

the Internet at http://

www.regulations.gov by searching for 

and locating Docket No. FAA–2016– 

7263; or in person at the Docket 

Management Facility between 9 a.m. 

and 5 p.m. Monday through Friday, 

except Federal holidays. The AD docket 

contains this AD, the regulatory 

evaluation, any comments received, and 

other information. The street address for 

the Docket Operations office (telephone 

800–647–5527) is in the ADDRESSES

section. Comments will be available in 

the AD docket shortly after receipt. 

FOR FURTHER INFORMATION CONTACT: 

Vladimir Ulyanov, Aerospace Engineer, 

International Branch, ANM–116, 

Transport Airplane Directorate, FAA, 

1601 Lind Avenue SW., Renton, WA 

98057–3356; telephone 425–227–1138; 

fax 425–227–1149. 

SUPPLEMENTARY INFORMATION: 

Discussion 

On March 26, 2016, we issued AD 

2016–07–30, Amendment 39–18475 (81 

FR 21722, April 13, 2016) (‘‘AD 2016– 

07–30’’), for all Airbus Model A330– 

200, –200 Freighter, and –300 series 

airplanes; and all Airbus Model A340– 

200, –300, –500, and –600 series 

airplanes. AD 2016–07–30 was 

prompted by a report of blockage of 

AOA probes during climb, leading to 

activation of the Alpha Prot while the 

Mach number increased. This activation 

could cause a continuous nose-down 

pitch rate that cannot be stopped with 

backward sidestick input, even in the 

full backward position. For certain 

airplanes, AD 2016–07–30 required 

replacing certain AOA sensors (probes) 

with certain new AOA sensors. For 

certain other airplanes, AD 2016–07–30 

also required inspections and functional 

heat testing of certain AOA sensors for 

discrepancies, and replacement if 

necessary. We issued AD 2016–07–30 to 

prevent erroneous AOA information and 

Alpha Prot activation due to blocked 

AOA probes, which could result in a 

continuous nose-down command and 

loss of control of the airplane. 

Since we issued AD 2016–07–30, we 

received a report of a typographical 

error in the regulatory text of AD 2016– 

07–30. Paragraph (l) of AD 2016–07–30 

inadvertently referred to paragraph (g) 

and should have referred to paragraph 

(j), ‘‘Repetitive Inspections/Tests of 

Certain Thales AOA Sensors.’’ The 

intent of paragraph (l) of AD 2016–07– 

30 was to give credit for doing the 


rmajette on DSK2TPTVN1PROD with RULES