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— 


jstallworth on DSK7TPTVN1PROD with RULES
Federal Register / Vol. 81, No. 79 / Monday, April 25, 2016 / Rules and Regulations 24013 

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 


jstallworth on DSK7TPTVN1PROD with RULES
24014 Federal Register / Vol. 81, No. 79 / Monday, April 25, 2016 / Rules and Regulations 

1The 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. Maximum 

sideward 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 illustrating 

investments 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 


jstallworth on DSK7TPTVN1PROD with RULESER25AP16.011</GPH>