65618 Federal Register / Vol. 80, No. 207 / Tuesday, October 27, 2015 / Rules and Regulations 

the procedures specified in paragraph (k) of 

this AD. 

(i) Exception to the Service Information 

(1) Where Boeing Alert Service Bulletin 

747–53A2451, Revision 2, dated June 13, 

2014, specifies a compliance time ‘‘after the 

Revision 2 date of this service bulletin,’’ this 

AD requires compliance within the specified 

time after the effective date of this AD. 

(2) The Condition column of paragraph 

1.E., ‘‘Compliance,’’ of the Boeing Alert 

Service Bulletin 747–53A2451, Revision 2, 

dated June 13, 2014, refers to total flight 

cycles ‘‘as of the Revision 2 date of this 

service bulletin.’’ This AD, however applies 

to airplanes with the specified total flight 

cycles or total flight hours as of the effective 

date of this AD. 

(j) Credit for Previous Actions 

This paragraph provides credit for the 

inspections and repairs of the inner chord 

strap and angles of the station 800 frame 

assembly between stringer 14 and stringer 18 

required by paragraphs (g) and (h) of this AD, 

if those actions were performed before the 

effective date of this AD using Boeing Alert 

Service Bulletin 747–53A2451, Revision 1, 

dated November 10, 2005, which was 

incorporated by reference in AD 2006–12–12, 

Amendment 39–14638 (71 FR 33595, June 

12, 2006). 

(k) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Seattle Aircraft 

Certification Office (ACO), FAA, has the 

authority to approve AMOCs for this AD, if 

requested using the procedures found in 14 

CFR 39.19. In accordance with 14 CFR 39.19, 

send your request to your principal inspector 

or local Flight Standards District Office, as 

appropriate. If sending information directly 

to the manager of the ACO, send it to the 

attention of the person identified in 

paragraph (l)(1) of this AD. Information may 

be emailed to: 9-ANM-Seattle-ACO-AMOCRequests@faa.gov. 

(2) Before using any approved AMOC, 

notify your appropriate principal inspector, 

or lacking a principal inspector, the manager 

of the local flight standards district office/

certificate holding district office. 

(3) An AMOC that provides an acceptable 

level of safety may be used for any repair 

required by this AD if it is approved by the 

Boeing Commercial Airplanes Organization 

Designation Authorization (ODA) that has 

been authorized by the Manager, Seattle 

ACO, to make those findings. For a repair 

method to be approved, the repair must meet 

the certification basis of the airplane, and the 

approval must specifically refer to this AD. 

(4) AMOCs approved for AD 2007–16–08, 

Amendment 39–15147 (72 FR 44728, August 

9, 2007), are approved as AMOCs for the 

corresponding provisions of this AD. 

(l) Related Information 

(1) For more information about this AD, 

contact Bill Ashforth, Aerospace Engineer, 

Airframe Branch, ANM–120S, FAA, Seattle 

Aircraft Certification Office (ACO), 1601 Lind 

Avenue SW., Renton, WA 98057–3356; 

phone: 425–917–6432; fax: 425–917–6590; 

email: bill.ashforth@faa.gov. 

(2) Service information identified in this 

AD that is not incorporated by reference is 

available at the addresses specified in 

paragraphs (m)(3) and (m)(4) of this AD. 

(m) 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) Boeing Alert Service Bulletin 747– 

53A2451, Revision 2, dated June 13, 2014. 

(ii) Reserved. 

(3) For service information identified in 

this AD, contact Boeing Commercial 

Airplanes, Attention: Data & Services 

Management, P.O. Box 3707, MC 2H–65, 

Seattle, WA 98124–2207; telephone 206– 

544–5000, extension 1; fax 206–766–5680; 

Internet https://www.myboeingfleet.com. 

(4) You may view this service information 

at 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. 

(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 Renton, Washington, on October 

19, 2015. 

Jeffrey E. Duven, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2015–26979 Filed 10–26–15; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2015–4345; Directorate 

Identifier 2015–SW–049–AD; Amendment 

39–18306; AD 2015–22–02] 

RIN 2120–AA64 

Airworthiness Directives; Bell 

Helicopter Textron Canada Limited 

Helicopters 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule; request for 

comments. 

SUMMARY: We are superseding 

emergency airworthiness directive (AD) 

No. 2015–16–51 (Emergency AD 2015– 

16–51) for Bell Helicopter Textron 

Canada Limited (Bell) Model 429 

helicopters. Emergency AD 2015–16–51 

required inspections of each inboard 

and outboard tail rotor pitch link 

assembly for axial or radial bearing play, 

and if there was axial or radial bearing 

play, removing the tail rotor pitch link 

and inspecting for wear. Emergency AD 

2015–16–51 was prompted by several 

reports of worn tail rotor pitch link 

spherical bearings. We are issuing this 

supersedure to retain the inspection 

requirements in Emergency AD 2015– 

16–51 while revising the applicability 

and compliance time to clarify that all 

Bell Model 429 helicopters require 

recurring inspections regardless of 

hours time-in-service (TIS) accumulated 

on the helicopter. These actions are 

intended to prevent pitch link failure 

and subsequent loss of control of the 

helicopter. 

DATES: This AD becomes effective 

November 12, 2015. 

We must receive comments on this 

AD by December 28, 2015. 

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–2015– 

4345; 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 

Emergency AD, 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 

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 the referenced service 

information at the FAA, Office of the 


tkelley on DSK3SPTVN1PROD with RULES
Federal Register / Vol. 80, No. 207 / Tuesday, October 27, 2015 / Rules and Regulations 65619 

Regional Counsel, Southwest Region, 

10101 Hillwood Pkwy, Room 6N–321, 

Fort Worth, TX 76177. 

FOR FURTHER INFORMATION CONTACT: 

David Hatfield, Aviation Safety 

Engineer, Safety Management Group, 

Rotorcraft Directorate, FAA, 10101 

Hillwood Pkwy, Fort Worth, TX 76177; 

telephone (817) 222–5110; email 

david.hatfield@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 

Transport Canada, which is the 

aviation authority for Canada, issued 

Emergency AD No. CF–2015–16, dated 

July 2, 2015, to correct an unsafe 

condition for Bell Model 429 

helicopters. Transport Canada advised 

that in-service reports showed that the 

tail rotor pitch link spherical bearings 

have experienced early and accelerated 

wear. On three occasions, bearings were 

found worn beyond limits during preflight inspections, showing a radial and 

axial play that was easily detectable. In 

one case, the spherical bearing 

separated from the tail rotor pitch link, 

resulting in damage to the tail rotor 

blade pitch horn assembly. In another 

case, the spherical bearing had been 

inspected and found acceptable during 

a maintenance inspection; about ‘‘1 

hour air time’’ later, it was found worn 

beyond limits during a pre-flight 

inspection. 

On August 6, 2015, we issued 

Emergency AD 2015–16–51, which was 

made immediately effective to all 

known U.S. owners and operators of 

Bell Model 429 helicopters. Emergency 

AD 2015–16–51 required, before further 

flight and thereafter at intervals not to 

exceed 50 hours TIS, inspecting each 

inboard and outboard tail rotor pitch 

link assembly for axial or radial bearing 

play. Emergency AD 2015–16–51 also 

required, if there was axial or radial 

bearing play, removing the tail rotor 

pitch link and performing a dimensional 

inspection for wear. Finally, Emergency 

AD 2015–16–51 required, if wear 

exceeded the allowable limits, replacing 

the tail rotor pitch link assembly. 

Actions Since Emergency AD 2015–16– 

51 Was Issued 

On the same day that we issued 

Emergency AD 2015–16–51, Transport 

Canada issued a revised Emergency AD 

No. CF–2015–16R1, dated August 6, 

2015, changing the applicability and 

compliance time to clarify that the 

inspections are required for all Model 

429 helicopters. Transport Canada 

advises of the possibility that some 

operators would conclude that no action 

was required for low time helicopters. 

Transport Canada Emergency AD No. 

CF–2015–16R1 removes the following 

language from the applicability so that 

it applies to all Model 429 helicopters 

regardless of time: ‘‘that have 

accumulated 50 hours air time or more.’’ 

It also adds language to the compliance 

time so that the corrective actions must 

be accomplished within 10 hours air 

time ‘‘or before exceeding 60 hours air 

time since new, whichever occurs 

later.’’ Therefore, we are issuing this AD 

to make similar revisions. 

FAA’s Determination 

These helicopters have been approved 

by Transport Canada and are 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 its 

Emergency 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 develop on other 

helicopters of this same type design. 

Related Service Information 

Bell issued Alert Service Bulletin 

429–15–16, dated February 18, 2015 

(ASB) for Bell Model 429 helicopters, S/ 

N 57001 and subsequent, which have 

accumulated more than 50 hours. The 

ASB specifies inspecting both inboard 

and outboard tail rotor pitch link 

assemblies for axial and radial play. If 

abnormal wear or bearing play is 

detected, the ASB specifies removing 

the affected tail rotor pitch link, 

performing a dimensional check of both 

axial and radial play, and replacing any 

tail rotor pitch link assembly 429–012– 

112–101 or –103 or pitch link bearing 

429–312–107–103 that exceeds the 

allowable limits. 

AD Requirements 

This AD retains the inspection 

requirements of Emergency AD 2015– 

16–51 but revises the applicability and 

compliance time. This AD applies to 

Model 429 helicopters regardless of 

accumulated TIS. The inspections in 

this AD are required before further flight 

for helicopters with 50 or more hours 

TIS and before accumulating 50 hours 

TIS for helicopters with less than 50 

hours TIS. 

Differences Between This AD and the 

Transport Canada Emergency AD 

The Transport Canada Emergency AD 

requires compliance within 10 hours 

TIS or before exceeding 60 hours air 

time, whichever occurs later. This AD 

requires compliance before further flight 

for helicopters with 50 or more hours 

TIS. For helicopters with less than 50 

hours TIS, this AD requires compliance 

before the helicopter accumulates 50 

hours TIS. 

Interim Action 

We consider this AD to be an interim 

action. If final action is later identified, 

we might consider further rulemaking 

then. 

Costs of Compliance 

We estimate that this AD affects 54 

helicopters of U.S. Registry. We estimate 

that operators may incur the following 

costs in order to comply with this AD. 

Labor costs are estimated at $85 per 

work hour. It will take about 2 work 

hours to do the inspections at an 

estimated cost of $170 per helicopter or 

$9,180 for the fleet per inspection cycle. 

Replacing a tail rotor pitch link 

assembly will take 4 work hours and 

required parts will cost $2,685 for a total 

cost of $3,025 per helicopter. 

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 found and continue to 

find that the risk to the flying public 

justifies waiving notice and comment 

prior to adopting this rule because the 

previously described unsafe condition 

can adversely affect the controllability 


tkelley on DSK3SPTVN1PROD with RULES
65620 Federal Register / Vol. 80, No. 207 / Tuesday, October 27, 2015 / Rules and Regulations 

of the helicopter, and the initial 

required corrective actions must be 

accomplished before further flight or 

before accumulating 50 hours TIS, 

depending upon the hours TIS 

accumulated on the helicopter. 

Since it was found that immediate 

corrective action was required, notice 

and opportunity for prior public 

comment before issuing this AD were 

impracticable and contrary to the public 

interest, and good cause existed to make 

the AD effective immediately by 

Emergency AD 2015–16–51, issued on 

August 6, 2015, to all known U.S. 

owners and operators of these 

helicopters. These conditions still exist 

and the Emergency AD is hereby 

superseded. 

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); 

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): 

2015–22–02 Bell Helicopter Textron 

Canada Limited: Amendment 39–18306; 

Docket No. FAA–2015–4345; Directorate 

Identifier 2015–SW–049–AD. 

(a) Applicability 

This AD applies to Model 429 helicopters 

with a pitch link assembly part number 429– 

012–112–101 or –103 installed, certificated 

in any category. 

(b) Unsafe Condition 

This AD defines the unsafe condition as a 

worn pitch link. This condition, if not 

detected and corrected, could result in pitch 

link failure and subsequent loss of control of 

the helicopter. 

(c) Affected ADs 

This AD supersedes Emergency AD 2015– 

16–51, Directorate Identifier 2015–SW–23– 

AD, dated August 6, 2015. 

(d) Effective Date 

This AD becomes effective November 12, 

2015. 

(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 

(1) For helicopters with 50 or more hours 

time-in-service (TIS), before further flight, 

and for helicopters with less than 50 hours 

TIS, before accumulating 50 hours TIS, 

inspect each inboard and outboard tail rotor 

pitch link assembly for axial or radial bearing 

play. If there is axial or radial bearing play, 

remove the tail rotor pitch link and perform 

a dimensional inspection for wear. If there is 

wear that exceeds the allowable limits, 

replace the tail rotor pitch link assembly. 

(2) Thereafter, at intervals not to exceed 50 

hours TIS, repeat the inspections required by 

paragraph (f)(1) of this AD. 

(g) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Safety Management 

Group, FAA, may approve AMOCs for this 

AD. Send your proposal to: David Hatfield, 

Aviation Safety Engineer, Safety Management 

Group, Rotorcraft Directorate, FAA, 10101 

Hillwood Pkwy., Fort Worth, TX 76177; 

telephone (817) 222–5110; email 9-ASWFTW-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. 

(h) Additional Information 

(1) Bell Helicopter Alert Service Bulletin 

429–15–16, dated February 18, 2015, which 

is not incorporated by reference, contains 

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 the referenced 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 

Transport Canada Emergency AD No. CF– 

2015–16R1, dated August 6, 2015. You may 

view the Transport Canada Emergency AD on 

the Internet at http://www.regulations.gov in 

Docket No. FAA–2015–4345. 

(i) Subject 

Joint Aircraft Service Component (JASC) 

Code: 6720 Tail Rotor Control System. 

Issued in Fort Worth, Texas, on October 16, 

2015. 

Lance T. Gant, 

Manager, Rotorcraft Directorate, Aircraft 

Certification Service. 

[FR Doc. 2015–27137 Filed 10–26–15; 8:45 am] 

BILLING CODE 4910–13P 


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