Federal Register / Vol. 81, No. 21 / Tuesday, February 2, 2016 / Rules and Regulations 5367 

Issued in Renton, Washington, on January 

20, 2016. 

Michael Kaszycki, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2016–01741 Filed 2–1–16; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2016–2068; Directorate 

Identifier 2016–SW–002–AD; Amendment 

39–18387; AD 2016–02–06] 

RIN 2120–AA64 

Airworthiness Directives; Bell 

Helicopter Textron Canada Limited 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule; request for 

comments. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for Bell 

Helicopter Textron Canada Limited 

(Bell) Model 429 helicopters. This AD 

requires inspecting each tail rotor (T/R) 

pitch link (link) bearing bore for 

corrosion and pitting and either 

replacing the T/R link or applying 

sealant. This AD also requires a 

recurring inspection of the sealant and 

repeating the inspections for corrosion 

and pitting if any sealant is missing. 

This AD is prompted by an incident in 

which a helicopter experienced an inflight failure of a T/R link. These actions 

are intended to detect corrosion or 

pitting and to prevent failure of a T/R 

link and subsequent loss of control of 

the helicopter. 

DATES: This AD becomes effective 

February 2, 2016. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain document listed in this AD 

as of February 2, 2016. 

We must receive comments on this 

AD by April 4, 2016. 

ADDRESSES: You may send comments by 

any of the following methods: 

• Federal eRulemaking Docket: Go to 

http://www.regulations.gov. Follow the 

online instructions for sending your 

comments electronically. 

• Fax: 202–493–2251. 

• Mail: Send comments to the U.S. 

Department of Transportation, Docket 

Operations, M–30, West Building 

Ground Floor, Room W12–140, 1200 

New Jersey Avenue SE., Washington, 

DC 20590–0001. 

• Hand Delivery: Deliver to the 

‘‘Mail’’ address between 9 a.m. and 5 

p.m., Monday through Friday, except 

Federal holidays. 

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– 

2068; 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 Transport Canada 

AD, the incorporated by reference 

service information, the economic 

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 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. 

FOR FURTHER INFORMATION CONTACT: Matt 

Fuller, Senior Aviation Safety Engineer, 

Safety Management Group, Rotorcraft 

Directorate, FAA, 10101 Hillwood 

Pkwy, Fort Worth, TX 76177; telephone 

(817) 222–5110; email matthew.fuller@

faa.gov. 

SUPPLEMENTARY INFORMATION: 

Comments Invited 

This AD is a final rule that involves 

requirements affecting flight safety, and 

we did not provide you with notice and 

an opportunity to provide your 

comments prior to it becoming effective. 

However, we invite you to participate in 

this rulemaking by submitting written 

comments, data, or views. We also 

invite comments relating to the 

economic, environmental, energy, or 

federalism impacts that resulted from 

adopting this AD. The most helpful 

comments reference a specific portion of 

the AD, explain the reason for any 

recommended change, and include 

supporting data. To ensure the docket 

does not contain duplicate comments, 

commenters should send only one copy 

of written comments, or if comments are 

filed electronically, commenters should 

submit them only one time. We will file 

in the docket all comments that we 

receive, as well as a report summarizing 

each substantive public contact with 

FAA personnel concerning this 

rulemaking during the comment period. 

We will consider all the comments we 

receive and may conduct additional 

rulemaking based on those comments. 

Discussion 

We are adopting a new AD for Bell 

Model 429 helicopters with a T/R link 

part number (P/N) 429–012–112–101, 

–101FM, –103, or –103FM installed. 

This AD requires inspecting each T/R 

link bearing bore for any aluminum 

oxide corrosion and then cleaning the 

affected area of the T/R link and 

inspecting for any pitting. If there is any 

corrosion or any pitting, this AD 

requires replacing the T/R link. If there 

is no corrosion or pitting, this AD 

requires applying corrosion preventative 

sealant. This AD also requires a 

recurring inspection of the sealant, and 

repeating the inspection for corrosion 

and pitting if any sealant is missing. 

This AD was prompted by AD No. 

CF–2016–01, dated January 5, 2016, 

issued by Transport Canada, which is 

the aviation authority for Canada, to 

correct an unsafe condition for Bell 

Model 429 helicopters. Transport 

Canada advises of an incident in which 

a T/R link on a Model 429 helicopter 

failed, causing vibration and difficulty 

controlling the helicopter. According to 

Transport Canada, the failure was 

caused by a crack that had initiated at 

a corrosion pit between the roll staked 

lip of the bearing and the beveled edge 

of the link. Transport Canada further 

states deficiencies in the application of 

corrosion resistant finishes to the link 

during manufacturing caused the 

corrosion. 

This condition, if not detected, could 

result in failure of a link and loss of 

control of the helicopter. For these 

reasons, Transport Canada AD No. CF– 

2016–01 requires inspection of the T/R 

link and replacement of any link with 

corrosion. The Transport Canada AD 

also requires application of corrosion 

preventative sealant and reidentification of the T/R link. 

FAA’s Determination 

This helicopter has been approved by 

the aviation authority of Canada and is 

approved for operation in the United 

States. Pursuant to our bilateral 

agreement with Canada, Transport 

Canada, its technical representative, has 

notified us of the unsafe condition 

described in the Canadian AD. We are 

issuing this AD because we evaluated 

all information provided by Transport 

Canada and determined the unsafe 

condition exists and is likely to exist or 


wgreen on DSK2VPTVN1PROD with RULES
5368 Federal Register / Vol. 81, No. 21 / Tuesday, February 2, 2016 / Rules and Regulations 

develop on other helicopters of the same 

type design. 

Related Service Information Under 1 

CFR Part 51 

Bell Helicopter issued Alert Service 

Bulletin 429–15–26, dated December 7, 

2015 (ASB), which advises of receiving 

reports of corrosion on T/R links 

between the roll staked lip of bearing P/ 

N 429–312–107–103 and the beveled 

edge of T/R link P/N 429–012–112–101/ 

–103. The ASB specifies, within 10 

flight hours or before March 7, 2016, an 

inspection with 10X magnification of all 

8 T/R link bearing bores between the 

roll staked lip of the bearing outer race 

and the link bearing bore for corrosion. 

If there is corrosion, the ASB specifies 

replacing the link. If there is no 

corrosion, the ASB specifies cleaning 

the area and performing a second 

inspection with 10X magnification. If 

there is corrosion, the ASB specifies 

replacing the link. If there is no 

corrosion, the ASB specifies removing 

the torque stripe, cleaning the area, and 

applying corrosion preventative sealant. 

The ASB also specifies re-identifying 

the P/Ns as 429–012–112–101FM and 

429–012–112–103FM. Further, the ASB 

specifies, at intervals of 50 flight hours 

after the initial actions, an inspection of 

the sealant and reapplication if the 

sealant is damaged. 

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. 

AD Requirements 

This AD requires, within 10 hours 

time-in-service (TIS), without first 

cleaning the T/R link bearing bores, 

using 10X or higher magnification to 

inspect each T/R link bearing bore for 

any aluminum oxide corrosion 

extruding from between the roll staked 

lip of the bearing outer race and the link 

bearing bore. If there is any aluminum 

oxide corrosion, this AD requires 

replacing the T/R link before further 

flight. If there is no corrosion, this AD 

requires cleaning the T/R link bearing 

bores and inspecting for any pitting. If 

there is any pitting, this AD requires 

replacing the T/R link before further 

flight. If there is no pitting, this AD 

requires applying corrosion preventative 

sealant. Within 50 hours TIS and 

thereafter at intervals not to exceed 50 

hours TIS, this AD requires inspecting 

the corrosion preventative sealant of 

each T/R link by using 10X or higher 

magnification. If the corrosion 

preventative sealant is missing, this AD 

requires performing the inspections for 

any aluminum oxide corrosion and 

pitting. 

Differences Between This AD and the 

Transport Canada AD 

This AD only applies to helicopters 

with certain link P/Ns installed. The 

Transport Canada AD does not specify 

link P/Ns. This AD requires inspecting 

the bearing bores for any pitting after 

cleaning the T/R link, while the 

Transport Canada AD requires 

inspecting for corrosion after cleaning 

the T/R link. This AD requires 

inspecting the sealant with 10X or 

higher magnification, while the 

Transport Canada AD does not specify 

any magnification. This AD does not 

require re-identifying the P/N of the 

link, whereas the Transport Canada AD 

does. As part of the recurring inspection 

of the corrosion preventative sealant, if 

the sealant is missing, this AD requires 

repeating the inspections for aluminum 

oxide corrosion and pitting to ensure 

part integrity before reapplying sealant. 

The Transport Canada AD only specifies 

reapplying sealant if the sealant is 

damaged. 

Costs of Compliance 

We estimate that this AD affects 73 

helicopters of U.S. Registry. We estimate 

that operators may incur the following 

costs in order to comply with this AD. 

We estimate the cost of labor at $85 per 

work-hour. 

Inspecting the set of T/R links (eight 

bearings) for corrosion will take about 

one work-hour for an estimated cost of 

$85 per helicopter and $6,205 for the 

U.S. fleet. Cleaning and inspecting the 

set of T/R links for pitting will take 

about one work-hour for an estimated 

cost of $85 per helicopter. Replacing a 

T/R link will require no additional 

work-hours after inspection and 

required parts cost $2,739 for an 

estimated replacement cost of $2,739 

per T/R link. Removing the torque 

stripe, cleaning, and applying sealant to 

the set of T/R links will take about one 

work-hour with a negligible parts cost 

for an estimated cost of $85 per 

helicopter. Inspecting the sealant on a 

set of T/R links will take about one 

work-hour for an estimated cost of $85 

per helicopter and $6,205 for the U.S. 

fleet per inspection cycle. 

According to Bell Helicopter’s service 

information some of the costs of this AD 

may be covered under warranty, thereby 

reducing the cost impact on affected 

individuals. We do not control warranty 

coverage by Bell Helicopter. 

Accordingly, we have included all costs 

in our cost estimate. 

FAA’s Justification and Determination 

of the Effective Date 

Providing an opportunity for public 

comments prior to adopting these AD 

requirements would delay 

implementing the safety actions needed 

to correct this known unsafe condition. 

Therefore, we find that the risk to the 

flying public justifies waiving notice 

and comment prior to the adoption of 

this rule because the unsafe condition 

can adversely affect control of the 

helicopter, and certain required 

corrective actions must be accomplished 

within 10 hours TIS. 

Since an unsafe condition exists that 

requires the immediate adoption of this 

AD, we determined that notice and 

opportunity for public comment before 

issuing this AD are impracticable and 

contrary to the public interest and that 

good cause exists for making this 

amendment effective in less than 30 

days. 

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 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, 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); 


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Federal Register / Vol. 81, No. 21 / Tuesday, February 2, 2016 / Rules and Regulations 5369 

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): 

2016–02–06 Bell Helicopter Textron 

Canada Limited: Amendment 39–18387; 

Docket No. FAA–2016–2068; Directorate 

Identifier 2016–SW–002–AD. 

(a) Applicability 

This AD applies to Bell Helicopter Textron 

Canada Limited Model 429 helicopters with 

a tail rotor (T/R) pitch link (link) part number 

(P/N) 429–012–112–101, –101FM, –103, or 

–103FM installed, certificated in any 

category. 

(b) Unsafe Condition 

This AD defines the unsafe condition as 

failure of a T/R link. This condition could 

result in loss of T/R flight control and 

subsequent loss of control of the helicopter. 

(c) Effective Date 

This AD becomes effective February 2, 

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 

(1) For T/R link P/N 429–012–112–101 and 

429–012–112–103, within 10 hours time-inservice (TIS): 

(i) Remove each T/R link assembly. Prior 

to cleaning the T/R link bearing bores, using 

10X or higher power magnification, inspect 

each T/R link bearing bore for aluminum 

oxide corrosion extruding from between the 

roll staked lip of the bearing outer race and 

the link bearing bore. Aluminum oxide 

corrosion appears as a white crystalline 

material in contrast with the black finish and 

any accumulated soot. An example of this 

corrosion is shown in Figure 1 of Bell 

Helicopter Alert Service Bulletin 429–15–26, 

dated December 7, 2015 (ASB 429–15–26). 

(ii) If there is any aluminum oxide 

corrosion, replace the T/R link before further 

flight. 

(iii) If there is no aluminum oxide 

corrosion, clean each T/R link bearing bore 

with isopropyl alcohol and inspect for 

pitting. 

(A) If there is any pitting, replace the T/ 

R link before further flight. 

(B) If there is no pitting, apply corrosion 

preventative sealant by following the 

Accomplishment Instructions, paragraph 5. 

of Part I, of ASB 429–15–26. 

(2) For all T/R links listed in paragraph (a) 

of this AD, within 50 hours TIS and 

thereafter at intervals not to exceed 50 hours 

TIS, using 10X or higher power 

magnification, inspect each T/R link bearing 

bore for missing corrosion preventative 

sealant. If any corrosion preventative sealant 

is missing, perform the actions in paragraph 

(e)(1)(i) through (e)(1)(iii) of this AD before 

further flight. 

(3) Do not install T/R link P/N 429–012– 

112–101 or –103 on any helicopter before 

complying with the actions in paragraph 

(e)(1) of this AD. 

(f) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Safety Management 

Group, FAA, may approve AMOCs for this 

AD. Send your proposal to: Matt Fuller, 

Senior Aviation Safety Engineer, Safety 

Management 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. 

(g) Additional Information 

The subject of this AD is addressed in 

Transport Canada AD CF–2016–01, dated 

January 5, 2016. You may view the Transport 

Canada AD on the Internet at http://

www.regulations.gov by searching for and 

locating it in Docket No. FAA–2016–2068. 

(h) Subject 

Joint Aircraft Service Component (JASC) 

Code: 6400, Tail Rotor System. 

(i) Material Incorporated by Reference 

(1) The Director of the Federal Register 

approved the incorporation by reference 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) Bell Helicopter Alert Service Bulletin 

429–15–26, dated December 7, 2015. 

(ii) Reserved. 

(3) For Bell Helicopter 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/. 

(4) 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. 

(5) 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 January 22, 

2016. 

Scott A. Horn, 

Acting Manager, Rotorcraft Directorate, 

Aircraft Certification Service. 

[FR Doc. 2016–01747 Filed 2–1–16; 8:45 am] 

BILLING CODE 4910–13–P 

CONSUMER PRODUCT SAFETY 

COMMISSION 

16 CFR Part 1031 

[CPSC Docket No. CPSC–2013–0034] 

Commission Participation and 

Commission Employee Involvement in 

Voluntary Standards Activities 

AGENCY: Consumer Product Safety 

Commission. 

ACTION: Final rule. 

SUMMARY: The United States Consumer 

Product Safety Commission 

(‘‘Commission’’ or ‘‘CPSC’’) is issuing 

this final rule to amend the existing 

regulation on Commission participation 

and employee involvement in voluntary 

standards activities. Currently, 

Commission rules allow employees to 

participate in voluntary standard 

development groups on a non-voting 

basis and do not allow Commission 

employees to accept leadership 

positions in voluntary standard 

development groups. This final rule 

removes these restrictions and allows 

Commission employees to participate as 

voting members and to accept 

leadership positions in voluntary 

standard development groups, subject to 

prior approval by CPSC’s Office of the 

Executive Director (‘‘OEX’’). 

DATES: The final rule will become 

effective on March 3, 2016. 


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