## 24012 Federal Register / Vol. 81, No. 79 / Monday, April 25, 2016 / Rules and Regulations

(e) Compliance

You are responsible for performing each action required by this AD within the specified compliance time unless it has already been accomplished prior to that time.
(f) Required Actions

Before further flight: (1) Disassemble each servo actuator to gain access to the piston rod as shown in Figures 1 through 5 and by following the Accomplishment Instructions, paragraph 3.A., Part I., of Woodward HRT Alert Service Bulletin No. 141600–67–02, dated August 18, 2010 (Woodward ASB).

(2) Clean the entire piston rod and nut using acetone and a nylon bristle brush removing all contaminates to allow for inspection. Inspect the grind relief configuration for the piston rod and nut as shown in Figure 6 of the Woodward ASB. If the grind relief is unacceptable as shown in Figure 6, replace the piston rod and the nut with airworthy parts.

(3) Using a 10X or higher magnifying glass, visually inspect the nut for any corrosion or any damage to the threads. If you find any corrosion or any damage to the threads, replace the nut with an airworthy nut.

(4) Using a 10X or higher magnifying glass, visually inspect the piston rod as shown in Figure 7 of the Woodward ASB for any corrosion, visible lack of cadmium plate (gold or gray color), or damage to the piston rod. For the purposes of this AD, damage to the piston rod is defined as pitting, a visible scratch, a crack, or a visible abrasion.

(i) If there is any corrosion or visible lack of cadmium plate or any damage to the piston rod in the Critical Areas as shown in Figure 7 of the Woodward ASB, replace the servo actuator with servo actuator P/N 222– 382–001–111 or P/N 222–382–001–111FM before further flight.

(ii) If there is any corrosion or visible lack of cadmium plate on the piston rod in areas that are not considered Critical Areas as shown in Figure 7 of the Woodward ASB, rework the piston rod by removing any surface corrosion that has not penetrated into the base material by lightly buffing. Clean the part using acetone and a nylon bristle brush to remove any residue. Comply with paragraphs (f)(5) through (f)(6) of this AD. Within 1,200 hours time-in-service (TIS) or 1 year, whichever occurs first, replace the servo actuator with servo actuator P/N 222– 382–001–111 or P/N 222–382–001–111FM.

(iii) If there is any corrosion that is red or orange in color, magnetic particle inspect the piston rod for a crack.

(A) If there is a crack, replace the servo actuator with servo actuator, P/N 222–382– 001–111 or P/N 222–382–001–111FM before further flight.

(B) If there is no crack, comply with paragraphs (f)(5) through (f)(6) of this AD. Within 2,400 hours TIS or 2 years, whichever occurs first, replace the servo actuator with servo actuator P/N 222–382–001–111 or P/N 222–382–001–111FM.

(iv) If there is no corrosion, visible lack of cadmium plate, or damage to the piston rod, comply with paragraphs (f)(5) through (f)(6) of this AD. Within 3,000 hours TIS or 4 years, whichever occurs first, replace the servo actuator with servo actuator P/N 222–382– 001–111 or P/N 222–382–001–111FM.

(5) Inspect the portion of the piston rod for any absence of cadmium plating (bare base metal), as shown in Figure 7 of the Woodward ASB. If there is any bare base metal on the piston rod in this area, apply brush cadmium plating to all bare and reworked areas using SPS5070 or equivalent 0.0002 to 0.0005 inch thick and rework the piston rod by following the Accomplishment Instructions, paragraph C., Part III, C.1.1.1. through C.1.1.3., of the Woodward ASB.

(6) Reassemble the servo actuator by following the Accomplishment Instructions, paragraph C, Part III, 1.1.4. through 3.3.4. of the Woodward ASB.
(g) Credit for Actions Previously Completed

Compliance with the Woodward ASB or with AD 2010–19–51 (75 FR 71540, November 24, 2010) before the effective date of this AD is considered acceptable for compliance with the corresponding inspections specified in paragraph (f) of this AD. If you replaced the piston rod pursuant to the Woodward ASB or paragraph (d)(1) or (d)(3) of AD 2010–19–51, apply the requirements of paragraph (f)(4)(iv) of this AD. (h) Alternative Methods of Compliance (AMOCs)

(1) The Manager, Safety Management Group, FAA, may approve AMOCs for this AD. Send your proposal to: Matt Wilbanks, Aviation Safety Engineer, Regulations and Policy Group, Rotorcraft Directorate, FAA, 10101 Hillwood Pkwy., Fort Worth, TX 76177; telephone (817) 222–5110; email 9– ASW-FTW-AMOC-Requests@faa.gov.

(2) For operations conducted under a 14 CFR part 119 operating certificate or under 14 CFR part 91, subpart K, we suggest that you notify your principal inspector, or lacking a principal inspector, the manager of the local flight standards district office or certificate holding district office, before operating any aircraft complying with this AD through an AMOC.

(i) Additional Information

(1) Bell Alert Service Bulletin (ASB) No. 222–11–111 for Model 222 and 222B helicopters, ASB No. 222U–11–82 for Model 222U helicopters, ASB No. 230–11–43 for Model 230 helicopters, and ASB No. 430–11– 46 for Model 430 helicopters, all Revision A and all dated June 22, 2012, which are not incorporated by reference, contain additional information about the subject of this AD. For service information identified in this AD, contact Bell Helicopter Textron Canada Limited, 12,800 Rue de l’Avenir, Mirabel, Quebec J7J1R4; telephone (450) 437–2862 or (800) 363–8023; fax (450) 433–0272; or at http://www.bellcustomer.com/files/. You may review a copy of the service information at the FAA, Office of the Regional Counsel, Southwest Region, 10101 Hillwood Pkwy., Room 6N–321, Fort Worth, TX 76177.

(2) The subject of this AD is addressed in the Transport Canada Civil Aviation (TCCA) AD No. CF–2010–29R1, dated July 26, 2012. You may view the TCCA AD on the Internet
at http://www.regulations.gov in Docket No. FAA–2013–0734. (j) Subject Joint Aircraft Service Component (JASC) Code: 6730, Rotorcraft Servo System.
(k) 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.

(3) The following service information was approved for IBR on December 9, 2010 (75 FR 71540, November 24, 2010).

(i) Woodward HRT Alert Service Bulletin No. 141600–67–02, dated August 18, 2010.

(ii) Reserved. (4) For Woodward HRT service information identified in this AD, contact Bell Helicopter Textron Canada Limited, 12,800 Rue de l’Avenir, Mirabel, Quebec J7J1R4; telephone (450) 437–2862 or (800) 363–8023; fax (450) 433–0272; or at http:// www.bellcustomer.com/files/.

(5) You may view this service information at FAA, Office of the Regional Counsel, Southwest Region, 10101 Hillwood Pkwy., Room 6N–321, Fort Worth, TX 76177. For information on the availability of this material at the FAA, call (817) 222–5110.

(6) You may view this service information that is incorporated by reference 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 Fort Worth, Texas, on April 13,
2016. Scott A. Horn, Acting Manager, Rotorcraft Directorate, Aircraft Certification Service.

[FR Doc. 2016–09236 Filed 4–22–16; 8:45 am]

**BILLING CODE 4910–13–P**



### DEPARTMENT OF TRANSPORTATION

**Federal Aviation Administration**

**14 CFR Part 39**

**[Docket No. FAA–2016–0183; Directorate Identifier 2015–SW–016–AD;Amendment**  **39–18498; AD 2016–08–21]**

**RIN 2120–AA64**



### Airworthiness Directives; Kaman **Aerospace Corporation**

**AGENCY** 

### : Federal Aviation Administration (FAA), DOT.

**ACTION** 

### : Final rule.

**SUMMARY** 

### : We are adopting a new airworthiness directive (AD) for Kaman Aerospace Corporation (Kaman) Model K–1200 helicopters. This AD requires revising the ‘‘Flight Limitations—NO LOAD’’ and ‘‘Flight Limitations—


## 24013 Federal Register / Vol. 81, No. 79 / Monday, April 25, 2016 / Rules and Regulations

LOAD’’ sections of the rotorcraft flight manual (RFM). This AD was prompted by a report of certain flight maneuvers that may lead to main rotor (M/R) blade to opposing hub contact. These actions are intended to prevent damage to the M/R flight controls and subsequent loss of control of the helicopter.

**DATES** 

### : This AD is effective May 31,
2016.

**ADDRESSES** 

### : For service information identified in this final rule, contact Kaman Aerospace Corporation, Old Windsor Rd., P.O. Box 2, Bloomfield, Connecticut 06002–0002; telephone (860) 242–4461; fax (860) 243–7047; or
at http://www.kamanaero.com. You may review a copy of 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 on the Internet at http:// www.regulations.gov by searching for and locating Docket No. FAA–2016– 0183; or in person at the Docket Operations Office between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this AD, the economic evaluation, any comments received, and other information. The street address for the Docket Operations Office (phone: 800–647–5527) is U.S. Department of Transportation, Docket Operations Office, M–30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE., Washington, DC 20590.

**FOR FURTHER INFORMATION CONTACT**

### : Kirk Gustafson, Aviation Safety Engineer, Boston Aircraft Certification Office, Engine & Propeller Directorate, FAA, 1200 District Avenue, Burlington, Massachusetts 01803; telephone (781) 238–7190; email kirk.gustafson@faa.gov.

**SUPPLEMENTARY INFORMATION** 

### :

Discussion

On January 21, 2016, at 81 FR 3344, the Federal Register published our notice of proposed rulemaking (NPRM), which proposed to amend 14 CFR part 39 by adding an AD that would apply to Kaman Model K–1200 helicopters. The NPRM proposed to require revising the ‘‘Flight Limitations–NO LOAD’’ and ‘‘Flight Limitations–LOAD’’ sections of the RFM by inserting a warning and limitations about rearward to forward flight, establishing maximum rearward and sideward flight speeds, and prohibiting weather-vanning takeoffs and departures to turn the helicopter. The NPRM was prompted by a report of a Model K–1200 helicopter turning suddenly and causing blade contact with the hub. The report suggests that a rapid aircraft yaw rate and subsequent yaw arresting maneuver may cause low clearance of the M/R blades with the opposing M/R hub. This condition could cause an M/R blade to strike the opposing rotor’s flight controls. The proposed requirements were intended to prevent damage to the M/R flight controls and subsequent loss of control of the helicopter.

The NPRM published with the previous mailing address for the Boston Aircraft Certification Office. We have revised this contact information in this final rule to reflect the new mailing address.

Comments

We gave the public the opportunity to participate in developing this AD, but we did not receive any comments on the NPRM (81 FR 3344, January 21, 2016).

FAA’s Determination

We have reviewed the relevant information and determined that an unsafe condition exists and is likely to exist or develop on other products of the same type design and that air safety and the public interest require adopting the AD requirements as proposed.

Related Service Information

Kaman has issued Kaman K–1200 RFM, Revision 5, dated April 14, 2015. This revision of the limitations section of the RFM inserts, for both load operations and no load operations, a warning and limitations about departing from rearward to forward flight, a maximum rearward flight speed of 25 knots, a maximum sideward flight speed of 17 knots, and a prohibition on weather-vanning takeoffs and departures as a method to turn aircraft. Costs of Compliance

We estimate that this AD will affect 16 helicopters of U.S. Registry. We estimate that operators may incur the following costs in order to comply with this AD. At an average labor rate of $85 per work-hour, we expect revising the RFM will require 0.5 work-hour, for cost of about $43 per helicopter, or $688 for the U.S. fleet. 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.

We prepared an economic evaluation of the estimated costs to comply with this AD and placed it in the AD docket. 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 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 (AD):
2016–08–21 Kaman Aerospace Corporation (Kaman): Amendment 39–18498; Docket


## 24014 Federal Register / Vol. 81, No. 79 / Monday, April 25, 2016 / Rules and Regulations

1 The regulations under section 4944(c) further provide that no purpose of a PRI may be to accomplish one or more of the purposes described in section 170(c)(2)(D) (attempting to influence legislation or participating in or intervening in any political campaign). Treas. Reg. § 53.4944– 3(a)(1)(iii). No. FAA–2016–0183; Directorate Identifier 2015–SW–016–AD.
(a) Applicability

This AD applies to Model K–1200 helicopters, certificated in any category.

(b) Unsafe Condition

This AD defines the unsafe condition as a main rotor (M/R) blade striking the opposing rotor’s flight controls. This condition could result in damage to the M/R flight controls and subsequent loss of control of the helicopter.

(c) Effective Date

This AD becomes effective May 31, 2016.
(d) Compliance

You are responsible for performing each action required by this AD within the specified compliance time unless it has already been accomplished prior to that time. (e) Required Actions
Within 10 hours time-in-service, revise Section 2 Limitations of the Kaman K–1200 Rotorcraft Flight Manual (RFM) by inserting a copy of this AD into the RFM or by making pen-and-ink changes, as follows:

(1) In the ‘‘Flight Limitations—NO LOAD’’ and ‘‘Flight Limitations—WITH LOAD’’ sections, add the information in Figure 1 to paragraph (e)(1) of this AD.

(2) In the ‘‘Flight Limitations—NO LOAD’’ and ‘‘Flight Limitations—WITH LOAD’’ sections, add the following: Maximum rearward flight speed: 25 knots. Maximumsideward flight speed: 17 knots. Weathervanning takeoffs/departures as a method to turn aircraft: Prohibited.
(f) Credit for Actions Previously Completed

Incorporating the changes contained in Kaman K–1200 RFM, Revision 5, dated April 14, 2015, before the effective date of this AD is considered acceptable for compliance with the corresponding actions specified in paragraph (e) of this AD.
(g) Alternative Methods of Compliance (AMOCs)

(1) The Manager, Boston Aircraft Certification Office, FAA, may approve AMOCs for this AD. Send your proposal to: Kirk Gustafson, Aviation Safety Engineer, Boston Aircraft Certification Office, Engine & Propeller Directorate, FAA, 1200 District Avenue, Burlington, Massachusetts 01803; telephone (781) 238–7190; email kirk.gustafson@faa.gov.

(2) For operations conducted under a 14 CFR part 119 operating certificate or under 14 CFR part 91, subpart K, we suggest that you notify your principal inspector, or lacking a principal inspector, the manager of the local flight standards district office or certificate holding district office before operating any aircraft complying with this AD through an AMOC.
(h) Additional Information

Kaman K–1200 RFM, Revision 5, dated April 14, 2015, which is not incorporated by reference, contains additional information about the subject of this final rule. For service information identified in this final rule, contact Kaman Aerospace Corporation, Old Windsor Rd., P.O. Box 2, Bloomfield, Connecticut 06002–0002; telephone (860) 242–4461; fax (860) 243–7047; or at http:// www.kamanaero.com. You may review a copy of this service information at the FAA, Office of the Regional Counsel, Southwest Region, 10101 Hillwood Pkwy., Room 6N– 321, Fort Worth, TX 76177.
(i) Subject

Joint Aircraft Service Component (JASC) Code: 6710, Main Rotor Control.

Issued in Fort Worth, Texas, on April 15,
2016. Scott A. Horn, Acting Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. 2016–09434 Filed 4–22–16; 8:45 am]

**BILLING CODE 4910–13–P**



### DEPARTMENT OF THE TREASURY

**Internal Revenue Service**

**26 CFR Part 53**

**[T.D. 9762]**

**RIN 1545–BK76**



### Examples of Program-Related **Investments**

**AGENCY** 

### : Internal Revenue Service (IRS), Treasury.

**ACTION** 

### : Final regulations.

**SUMMARY** 

### : This document contains final regulations that provide guidance to private foundations on program-related investments. The final regulations provide a series of examples illustratinginvestments that qualify as programrelated investments. In addition to private foundations, these final regulations affect foundation managers who participate in the making of program-related investments.

**DATES** 

### : These regulations are effective April 25, 2016.

**FOR FURTHER INFORMATION CONTACT**

### : Robin Ehrenberg at (202) 317–4086 (not a toll-free number).

**SUPPLEMENTARY INFORMATION** 

### : Background

This document contains amendments to 26 CFR part 53 under section 4944(a) of the Internal Revenue Code (Code). Section 4944(a) imposes an excise tax on a private foundation that makes an investment that jeopardizes the carrying out of its exempt purposes (a ‘‘jeopardizing investment’’). Section 4944(c) provides that investments that are program-related investments (‘‘PRIs’’) are not jeopardizing investments. Section 4944(c) defines a PRI as an investment: (1) The primary purpose of which is to accomplish one or more of the purposes described in section 170(c)(2)(B); and (2) no significant purpose of which is the production of income or the appreciation of property. 1



### The regulations under section 4944(c) provide that an investment is made primarily to accomplish one or more of the purposes described in section