### 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


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

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,


### 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