Federal Register / Vol. 79, No. 146 / Wednesday, July 30, 2014 / Proposed Rules 44147 

no further action is required by this 

paragraph. 

(2) If the resistance value is greater than 10 

milliOhms at the left-hand or right-hand 

wing, before further flight, do a general visual 

inspection for corrosion of the component 

interface and adjacent area, in accordance 

with the Accomplishment Instructions of 

Airbus Service Bulletin A320–57–1152, 

dated June 14, 2010. If any corrosion is found 

during the inspection, before further flight, 

repair the gravity fill fuel adaptor, in 

accordance with the Accomplishment 

Instructions of Airbus Service Bulletin A320– 

57–1152, dated June 14, 2010; except where 

Airbus Service Bulletin A320–57–1152, 

dated June 14, 2010, specifies to contact 

Airbus, before further flight, repair using a 

method approved by the Manager, 

International Branch, ANM–116, Transport 

Airplane Directorate, FAA; or the European 

Aviation Safety Agency (EASA); or Airbus’s 

EASA Design Organization Approval (DOA). 

If approved by the DOA, the approval must 

include the DOA-authorized signature. 

(h) New Requirement of This AD: 

Maintenance Check/Electrical Bonding Test 

and Corrective Action if Necessary 

For airplanes other than those identified in 

paragraph (g) of this AD: Within 24 months 

after the effective date of this AD, determine 

whether a corrosion repair has been done on 

an overwing refueling aperture, whereby a 

primer coating has been applied on the 

mating surface of the aperture flange. A 

maintenance records check is acceptable to 

make this determination, provided those 

records can conclusively determine whether 

a primer coat was applied. 

(1) If it is determined that a primer coating 

was applied on the mating surface of the 

aperture flange; or if a determination cannot 

be made, or the outcome is inconclusive: 

Within 24 months after the effective date of 

this AD do the electrical bonding test 

specified in paragraph (g) of this AD, and 

before further flight, all applicable actions 

specified in paragraph (g)(2) of this AD. 

(2) If it is determined that a corrosion 

repair has not been done, and a primer 

coating has not been applied on the mating 

surface of the aperture flange since first entry 

into service, no further action is required by 

this paragraph. 

(i) Corrosion Repair Provision 

As of the effective date of this AD, any 

corrosion repair done on an overwing 

refueling aperture on any airplane must be 

compliant with the repair requirements of 

paragraph (g)(2) of this AD. 

(j) Other FAA AD Provisions 

The following provisions also apply to this 

AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, International 

Branch, ANM–116, Transport Airplane 

Directorate, 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 International Branch, send it to ATTN: 

Sanjay Ralhan, Aerospace Engineer, 

International Branch, ANM–116, Transport 

Airplane Directorate, FAA, 1601 Lind 

Avenue SW., Renton, WA 98057–3356; 

telephone (425) 227–1405; fax (425) 227– 

1149. Information may be emailed to: 9- 

ANM-116-AMOC-REQUESTS@faa.gov. 

(i) 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. The AMOC 

approval letter must specifically reference 

this AD. 

(ii) AMOCs approved previously for AD 

2012–09–07, Amendment 39–17042 (77 FR 

28238, May 14, 2012), are approved as 

AMOCs for the corresponding provisions of 

this AD. 

(2) Contacting the Manufacturer: For any 

requirement in this AD to obtain corrective 

actions from a manufacturer, the action must 

be accomplished using a method approved 

by the Manager, International Branch, ANM– 

116, Transport Airplane Directorate, FAA; or 

the European Aviation Safety Agency 

(EASA); or Airbus’s EASA Design 

Organization Approval (DOA). If approved by 

the DOA, the approval must include the 

DOA-authorized signature. 

(k) Related Information 

(1) Refer to Mandatory Continuing 

Airworthiness Information (MCAI) EASA 

Airworthiness Directive 2013–0277R1, dated 

December 4, 2013, for related information. 

This MCAI may be found in the AD docket 

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

by searching for and locating Docket No. 

FAA–2014–0484. 

(2) For service information identified in 

this AD, contact Airbus, Airworthiness 

Office—EAS, 1 Rond Point Maurice Bellonte, 

31707 Blagnac Cedex, France; telephone +33 

5 61 93 36 96; fax +33 5 61 93 44 51; email 

account.airworth-eas@airbus.com; Internet 

http://www.airbus.com. You may view this 

service information at the 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. 

Issued in Renton, Washington, on July 13, 

2014. 

Jeffrey E. Duven, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2014–17930 Filed 7–29–14; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2014–0499; Directorate 

Identifier 2013–SW–061–AD] 

RIN 2120–AA64 

Airworthiness Directives; Bell 

Helicopter Textron Canada 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to adopt a new 

airworthiness directive (AD) for Bell 

Helicopter Textron Canada (BHTC) 

Model 430 helicopters to require 

inspecting the tail rotor control tube 

assembly (control tube) and either 

repairing or replacing the control tube. 

This proposed AD is prompted by two 

reports of failure of the control tube 

bonded clevis. The proposed actions are 

intended to prevent failure of a control 

tube bonded clevis, which could lead to 

failure of the control tube and 

subsequent loss of helicopter control. 

DATES: We must receive comments on 

this proposed AD by September 29, 

2014. 

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 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 proposed AD, the 

foreign authority’s 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 proposed AD, contact Bell 


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44148 Federal Register / Vol. 79, No. 146 / Wednesday, July 30, 2014 / Proposed Rules 

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, 

2601 Meacham Blvd., Room 663, Fort 

Worth, Texas 76137. 

FOR FURTHER INFORMATION CONTACT: Matt 

Fuller, Senior Aviation Safety Engineer, 

Safety Management Group, Rotorcraft 

Directorate, FAA, 2601 Meacham Blvd., 

Fort Worth, Texas 76137; telephone 

(817) 222–5110; email matthew.fuller@

faa.gov. 

SUPPLEMENTARY INFORMATION: 

Comments Invited 

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 might result 

from adopting the proposals in this 

document. The most helpful comments 

reference a specific portion of the 

proposal, 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 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 proposed rulemaking. 

Before acting on this proposal, we will 

consider all comments we receive on or 

before the closing date for comments. 

We will consider comments filed after 

the comment period has closed if it is 

possible to do so without incurring 

expense or delay. We may change this 

proposal in light of the comments we 

receive. 

Discussion 

Transport Canada Civil Aviation 

(TCCA), which is the aviation authority 

for Canada, has issued Canadian AD No. 

CF–2013–30, dated October 7, 2013, to 

correct an unsafe condition for BHTC 

Model 430 helicopters with control tube 

part number (P/N) 430–001–007–101. 

TCCA advises of two cases concerning 

failures of the control tube bonded 

clevis caused by cracking from control 

tube oscillation. TCCA states that this 

situation, if not corrected, could result 

in the loss of control of the helicopter. 

TCCA AD No. CF–2013–30 

consequently requires a one-time 

inspection of the control tube for 

damage and contacting BHTC for 

evaluation of the control tube if the 

damage exceeds allowable limits. If the 

tube is not damaged, the damage is 

within allowable limits, or BHTC 

Engineering determines the control tube 

can be returned to service, TCCA AD 

No. CF–2013–30 requires modifying the 

tube according to BHTC’s service 

information. TCCA AD No. CF–2013–30 

also requires replacing control tubes, 

P/N 430–001–007–101, with control 

tube, P/N 430–001–007–105, no later 

than 12 months from the effective date 

of its AD. 

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 its 

AD. We are proposing this AD because 

we evaluated all known relevant 

information and determined that an 

unsafe condition is likely to exist or 

develop on other products of the same 

type design. 

Related Service Information 

We reviewed Bell Helicopter Alert 

Service Bulletin No. 430–13–51, dated 

September 3, 2013 (ASB), which states 

that BHTC received two reports of 

control tube, P/N 430–001–007–101, 

failing because the clevis failed due to 

fatigue caused by control tube 

oscillation. The ASB specifies a onetime inspection of control tube 

assembly, P/N 430–001–007–101, to 

verify if the tube has chaffing damage. 

Bell Helicopter Technical Bulletin 430– 

04–35, Revision B, dated March 20, 

2009, recommends that control tube, 

P/N 430–001–007–101, be replaced with 

control tube, P/N 430–001–007–105, if 

damage exists. 

Proposed AD Requirements 

This proposed AD would require: 

• Within 50 hours time-in-service 

(TIS), visually inspecting each control 

tube for damage, damage to the clevis, 

and to determine whether the clevis is 

correctly bonded to the control tube. 

• If a control tube and clevis have no 

damage or damage within acceptable 

limits and the clevis is correctly bonded 

to the control tube, repairing the control 

tube by applying tape. 

• If the control tube or clevis is 

damaged beyond acceptable limits or if 

the clevis is not correctly bonded, 

replacing control tube, P/N 430–001– 

007–101, with control tube, P/N 430– 

001–007–105. 

• Within 250 hours TIS after the 

effective date of this AD, replacing each 

control tube, P/N 430–001–007–101, 

with control tube, P/N 430–001–007– 

105. 

Differences Between This Proposed AD 

and the TCCA AD 

The TCCA AD requires submitting 

sketches of a control tube damaged 

beyond defined limits to BHTC for 

evaluation. BHTC then determines if the 

control tube can be returned to service. 

We make no such requirement in this 

proposed AD. 

Costs of Compliance 

We estimate that this proposed AD 

would affect 5 helicopters of U.S. 

Registry and that labor costs average $85 

a work hour. Based on these estimates, 

expect the following costs: 

• The cost of inspecting the control 

tube would be minimal. 

• Repairing the control tube would 

require 2 work-hours for a labor cost of 

$170. 

• Replacing control tube, P/N 430– 

001–007–101, with control tube, P/N 

430–001–007–105, would require 3 

work-hours for a labor cost of $255. 

Parts would cost $3,974 for a total cost 

per helicopter of $4,229. 

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 proposed AD 

would not have federalism implications 

under Executive Order 13132. This 

proposed AD would 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 


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Federal Register / Vol. 79, No. 146 / Wednesday, July 30, 2014 / Proposed Rules 44149 

responsibilities among the various 

levels of government. 

For the reasons discussed, I certify 

this proposed regulation: 

1. Is not a ‘‘significant regulatory 

action’’ under Executive Order 12866; 

2. Is not a ‘‘significant rule’’ under the 

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 proposed 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. 

The Proposed Amendment 

Accordingly, under the authority 

delegated to me by the Administrator, 

the FAA proposes to amend 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. Amend § 39.13 by adding the 

following new airworthiness directive 

(AD): 

Bell Helicopter Textron Canada: Docket No. 

FAA–2014–0499; Directorate Identifier 

2013–SW–061–AD. 

(a) Applicability 

This AD applies to Bell Helicopter Textron 

Canada (BHTC) Model 430 Helicopters, serial 

number 49001 through 49121, with control 

tube assembly (control tube), part number 

(P/N) 430–001–007–101, installed, 

certificated in any category. 

(b) Unsafe Condition 

This AD defines the unsafe condition as 

fatigue failure of a tail rotor control tube 

bonded clevis. This condition could result in 

failure of the tail rotor control tube and 

subsequent loss of helicopter control. 

(c) Comments Due Date 

We must receive comments by September 

29, 2014. 

(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) Within 50 hours time-in-service (TIS), 

visually inspect each control tube for any 

damage, for any damage to the clevis, and to 

determine whether the clevis is correctly 

bonded to the control tube. 

(i) If a control tube and clevis have no 

damage or damage within acceptable limits 

and the clevis is correctly bonded to the 

control tube, repair the control tube by 

applying tape in accordance the 

Accomplishment Instructions, Paragraph 5, 

of Bell Helicopter Alert Service Bulletin 430– 

13–51, dated September 3, 2013. 

(ii) If the control tube or clevis is damaged 

beyond acceptable limits or if the clevis is 

not correctly bonded to the control tube, 

replace control tube, P/N 430–001–007–101, 

with control tube, P/N 430–001–007–105. 

(2) Within 250 hours TIS, replace each 

control tube, P/N 430–001–007–101, with 

control tube, P/N 430–001–007–105. 

(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, 2601 Meacham Blvd., Fort Worth, 

Texas 76137; telephone (817) 222–5110; 

email matthew.fuller@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 

(1) Bell Helicopter Technical Bulletin 430– 

04–35, Revision B, dated March 20, 2009, 

which is not incorporated by reference, 

contains additional information about the 

subject of this AD. For service information, 

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, 2601 Meacham Blvd., 

Room 663, Fort Worth, Texas 76137. 

(2) The subject of this AD is addressed in 

the Transport Canada Civil Aviation (TCCA) 

AD No. CF–2013–30, dated October 7, 2013. 

You may view the TCCA AD on the Internet 

at http://www.regulations.gov in Docket No. 

FAA–2014–0499. 

(h) Subject 

Joint Aircraft Service Component (JASC) 

Code: 6720, Tail Rotor Control System. 

Issued in Fort Worth, Texas, on July 18, 

2014. 

S. Frances Cox, 

Acting Directorate Manager, Rotorcraft 

Directorate, Aircraft Certification Service. 

[FR Doc. 2014–17925 Filed 7–29–14; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF THE INTERIOR 

Bureau of Indian Affairs 

[K00103 12/13 A3A10; 134D0102DR– 

DS5A300000–DR.5A311.IA000113] 

25 CFR Part 83 

RIN 1076–AF18 

Federal Acknowledgment of American 

Indian Tribes 

AGENCY: Bureau of Indian Affairs, 

Interior. 

ACTION: Proposed rule; extension of 

comment period. 

SUMMARY: On May 22, 2014, the 

Department of the Interior announced 

the availability of a proposed rule to 

revise regulations governing the process 

and criteria by which the Secretary 

acknowledges an Indian tribe. We have 

since received several requests for 

extension of the comment period and 

additional public hearings. This notice 

extends the comment deadline by 60 

days and announces the addition of two 

more public hearings and two more 

tribal consultation sessions on the 

proposed rule. 

DATES: Comments on this rule must be 

received by September 30, 2014. See the 

SUPPLEMENTARY INFORMATION section of 

this notice for information on the public 

hearings and tribal consultations. 

ADDRESSES: You may submit comments 

by any of the following methods: 

• Federal rulemaking portal: http://

www.regulations.gov. The rule is listed 

under the agency name ‘‘Bureau of 

Indian Affairs.’’ The rule has been 

assigned Docket ID: BIA–2013–0007. 

• Email: consultation@bia.gov. 

Include the number 1076–AF18 in the 

subject line. 

• Mail or hand delivery: Elizabeth 

Appel, Office of Regulatory Affairs & 

Collaborative Action, U.S. Department 

of the Interior, 1849 C Street NW., MS 

3642, Washington, DC 20240. Include 

the number 1076–AF18 on the 

envelope. 

Please note that we will not consider 

or include in the docket for this 

rulemaking comments received after the 

close of the comment period (see DATES) 

or comments sent to an address other 

than those listed above. 

FOR FURTHER INFORMATION CONTACT: Ms. 

Elizabeth Appel, Director, Office of 

Regulatory Affairs & Collaborative 

Action, (202) 273–4680; 

elizabeth.appel@bia.gov. 

SUPPLEMENTARY INFORMATION: On May 

22, 2014, we announced the availability 

of a proposed rule to revise regulations 

governing the process and criteria by 


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