24010 Federal Register / Vol. 81, No. 79 / Monday, April 25, 2016 / Rules and Regulations 

definition of transparent at 10 CFR 

431.292. When determining whether or 

not a particular wall segment is 

transparent, transparency should be 

determined for the aggregate 

performance of all the materials 

between the refrigerated volume and the 

ambient environment; the composite 

performance of all those materials in a 

particular wall segment must meet the 

definition of transparent for that area be 

treated as transparent. 

(ii) Determination of non-transparent 

area. Determine the total surface area 

that is not transparent as the sum of all 

surface areas on the front side of a 

beverage vending machine that are not 

considered part of the transparent area, 

as determined in accordance with 

paragraph (j)(2)(i) of this section. 

Issued in Washington, DC, on February 9, 

2016. 

Kathleen Hogan, 

Deputy Assistant Secretary for Energy 

Efficiency, Energy Efficiency and Renewable 

Energy. 

[FR Doc. 2016–09555 Filed 4–22–16; 8:45 am] 

BILLING CODE 6450–01–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2013–0734; Directorate 

Identifier 2012–SW–080–AD; Amendment 

39–18494; AD 2016–08–17] 

RIN 2120–AA64 

Airworthiness Directives; Bell 

Helicopter Textron Canada Helicopters 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are superseding 

Airworthiness Directive (AD) 2010–19– 

51 for Bell Helicopter Textron Canada 

(Bell) Model 222, 222B, 222U, 230, and 

430 helicopters. AD 2010–19–51 

required inspecting parts of the main 

rotor hydraulic servo actuator (servo 

actuator) for certain conditions and 

replacing any unairworthy parts before 

further flight. This new AD requires 

installing a servo actuator with a new 

stainless steel piston rod. This AD was 

prompted by a collective servo actuator 

malfunction. We are issuing this AD to 

detect corrosion on a piston rod, which 

could result in failure of the servo 

actuator and consequent loss of 

helicopter control. 

DATES: This AD is effective May 31, 

2016. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain document listed in this AD 

as of December 9, 2010 (75 FR 71540, 

November 24, 2010). 

ADDRESSES: For service information 

identified in this final rule, 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 the referenced service 

information at the FAA, Office of the 

Regional Counsel, Southwest Region, 

10101 Hillwood Pkwy., Room 6N–321, 

Fort Worth, TX 76177. It is also on the 

Internet at http://www.regulations.gov 

by searching for and locating Docket No. 

FAA–2013–0734. 

Examining the AD Docket 

You may examine the AD docket on 

the Internet at http://

www.regulations.govby searching for 

and locating Docket No. FAA–2013– 

0734; 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 Transport Canada 

Civil Aviation (TCCA) AD, any 

incorporated-by-reference information, 

the economic 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: Matt 

Wilbanks, Aviation Safety Engineer, 

Regulations and Policy Group, 

Rotorcraft Directorate, FAA, 10101 

Hillwood Pkwy., Fort Worth, TX 76177; 

telephone (817) 222–5110; email 

matt.wilbanks@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Discussion 

On August 12, 2013, we issued a 

notice of proposed rulemaking (NPRM) 

that was published in the Federal 

Register on August 20, 2013 (78 FR 

51123). The NPRM proposed to remove 

AD 2010–19–51, Amendment 39–16523 

(75 FR 71540, November 24, 2010) and 

add a new AD for Bell Model 222, 222B, 

222U, 230, and 430 helicopters. The 

NPRM proposed to require inspecting 

servo actuator part number (P/N) 222– 

382–001–107 using a 10X or higher 

magnifying glass to determine whether 

the piston rod has any pitting or 

penetration of the base metal. If the 

piston rod had any pitting or 

penetration of the base metal, the NPRM 

proposed replacing servo actuator P/N 

222–382–001–107 with servo actuator 

P/N 222–382–001–111 or P/N 222–382– 

001–111FM. Thereafter, the NPRM 

proposed overhauling servo actuator P/ 

N 222–382–001–111 or P/N 222–382– 

001–111FM at intervals not to exceed 10 

years or 10,000 hours time-in-service 

(TIS), whichever comes first. The NPRM 

was prompted by AD No. CF–2010– 

29R1, dated July 26, 2012, issued by 

TCCA, which is the aviation authority 

for Canada. TCCA AD No. CF–2010– 

29R1 requires an inspection of the servo 

actuator and either overhauling or 

replacing the piston rod with a stainless 

steel piston rod. Replacement of the 

piston rod extends the overhaul interval 

of the servo actuator to 10,000 hours TIS 

or 10 years, whichever comes first. 

TCCA AD No. CF–2010–29R1 allows 

different compliance times for overhaul 

or replacement of the piston rod, 

depending on the condition of the 

piston rod when inspected. 

After the NPRM was published, we 

received comments from Bell requesting 

we mandate replacement of servo 

actuator P/N 222–382–001–107 with 

servo actuator part number P/N 222– 

382–001–111 even if no pitting or 

penetration of the base metal is found 

during the inspection, in accordance 

with the replacement provisions in its 

Alert Service Bulletin (ASB) 430–11–46, 

Revision A, dated June 20, 2012. In light 

of those comments, we determined that 

our AD should retain all of the 

inspection requirements of AD 2010– 

19–51 and also include compliance 

times specified in Revision A of the 

ASB for replacing servo actuator P/N 

222–382–001–107 with servo actuator 

P/N 222–382–001–111 or –111FM. 

Therefore, we revised the proposed 

actions accordingly. Because those 

changes expanded the scope of the 

original NPRM, we determined that it 

was necessary to reopen the comment 

period to provide additional 

opportunity for the public to comment. 

A supplemental notice of proposed 

rulemaking (SNPRM) was published in 

the Federal Register on June 16, 2015 

(80 FR 34332). 

Since the SNPRM was issued, the 

FAA Southwest Regional Office has 

relocated and a group email address has 

been established for requesting an FAA 

Alternative Method of Compliance for a 

helicopter of foreign design. We have 

updated this information throughout 

this AD. 

We have also removed the proposed 

paragraph (f)(7) from the Required 

Actions section, which would have 

required overhauling servo actuator P/N 

222–382–001–111 or P/N 222–382–001– 


jstallworth on DSK7TPTVN1PROD with RULES
Federal Register / Vol. 81, No. 79 / Monday, April 25, 2016 / Rules and Regulations 24011 

111FM at intervals not to exceed 10 

years or 10,000 hours TIS, whichever 

occurs first. Because replacement of 

servo actuator P/N 222–382–001–107 

with P/N 222–382–001–111 or –111FM 

corrects the unsafe condition, we have 

determined that AD action for this 

overhaul requirement is not appropriate. 

Comments 

We gave the public the opportunity to 

participate in developing this AD, but 

we received no comments on the 

SNPRM (80 FR 34332, June 16, 2015). 

FAA’s Determination 

These helicopters have been approved 

by the aviation authority of Canada and 

are approved for operation in the United 

States. Pursuant to our bilateral 

agreement with Canada, TCCA, its 

technical representative, has notified us 

of the unsafe condition described in the 

TCCA AD. We are issuing this AD 

because we evaluated all information 

provided by TCCA and determined the 

unsafe condition exists and is likely to 

exist or develop on other helicopters of 

these same type designs and that air 

safety and the public interest require 

adopting the AD requirements as 

proposed. 

Differences Between This AD and the 

TCCA AD 

The TCCA AD requires inspecting 

each servo actuator to determine the 

condition of the piston rod assembly no 

later than 5 hours upon receiving the 

original issue of its AD. This AD 

requires inspecting each servo actuator 

to determine the condition of the piston 

rod assembly before further flight. 

Related Service Information Under 1 

CFR Part 51 

We reviewed Woodward HRT Service 

Bulletin 141600–67–02, dated August 

18, 2010, which provides instructions 

for disassembling the servo actuator and 

for cleaning and inspecting the piston 

rod and nut. 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. 

Other Related Service Information 

We also reviewed Bell ASB 222–11– 

111 for Model 222 and 222B helicopters, 

ASB 222U–11–82 for Model 222U 

helicopters, ASB 230–11–43 for Model 

230 helicopters, and ASB 430–11–46 for 

Model 430 helicopters, all Revision A 

and all dated June 22, 2012. The ASBs 

contain, and require compliance with, 

Woodward HRT Service Bulletin 

141600–67–03, dated February 14, 2012, 

to upgrade the servo actuator by 

replacing the piston rod and then reidentifying the servo actuator dash 

number with ‘‘–111FM.’’ The 

compliance time for upgrading the servo 

actuator varies depending on the results 

of the inspections required by 

Woodward HRT Service Bulletin 

141600–67–02, dated August 18, 2010. 

The Bell ASBs also provide an 

alternative inspection procedure for 

servo actuator P/N 222–382–001–107 

that has not reached certain hours TIS 

and where the servo actuator cannot be 

upgraded. TCCA classified these ASBs 

as mandatory and issued AD No. CF– 

2010–29R1, dated July 26, 2012, to 

ensure the continued airworthiness of 

these helicopters. 

Costs of Compliance 

We estimate that this AD affects 146 

helicopters of U.S. Registry and that 

labor costs average $85 a work-hour. 

Based on these estimates, we expect the 

following costs: 

• Inspecting a servo actuator requires 

4 work-hours per actuator for a labor 

cost of $340. No parts are needed for a 

total cost of $1,020 per helicopter and 

$148,920 for the U.S. fleet given 3 

actuators per helicopter. 

• Replacing a servo actuator requires 

8 work-hours for a labor cost of $680. 

Parts cost $35,700 for a total cost of 

$36,380 per actuator. 

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 

We have determined that 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, 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 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) 

2010–19–51, Amendment 39–16523 (75 

FR 71540, November 24, 2010), and 

adding the following new AD: 

2016–08–17 Bell Helicopter Textron 

Canada: Amendment 39–18494; Docket 

No. FAA–2013–0734; Directorate 

Identifier 2012–SW–080–AD. 

(a) Applicability 

This AD applies to Bell Helicopter Textron 

Canada (Bell) Model 222, 222B, 222U, 230, 

and 430 helicopters, with a main rotor 

hydraulic servo actuator (servo actuator) part 

number (P/N) 222–382–001–107 installed, 

certificated in any category. 

(b) Unsafe Condition 

This AD defines the unsafe condition as 

corrosion or a nonconforming grind relief on 

the output piston rod assembly (piston rod). 

This condition could lead to failure of the 

piston rod, failure of the servo actuator, and 

subsequent loss of helicopter control. 

(c) Affected ADs 

This AD supersedes AD 2010–19–51, 

Amendment 39–16523 (75 FR 71540, 

November 24, 2010). 

(d) Effective Date 

This AD becomes effective May 31, 2016. 


jstallworth on DSK7TPTVN1PROD with RULES
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