8358 Federal Register / Vol. 79, No. 29 / Wednesday, February 12, 2014 / Proposed Rules 

requirements of the Paperwork Reduction 

Act unless that collection of information 

displays a current valid OMB Control 

Number. The OMB Control Number for this 

information collection is 2120–0056. Public 

reporting for this collection of information is 

estimated to be approximately 5 minutes per 

response, including the time for reviewing 

instructions, completing and reviewing the 

collection of information. All responses to 

this collection of information are mandatory. 

Comments concerning the accuracy of this 

burden and suggestions for reducing the 

burden should be directed to the FAA at: 800 

Independence Ave. SW., Washington, DC 

20591, Attn: Information Collection 

Clearance Officer, AES–200. 

(o) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Fort Worth Airplane 

Certification Office, 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 (p) of this AD. 

(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) AMOCs approved for AD 2010–17–18 

are approved as AMOCs for this AD. 

(p) Related Information 

(1) For more information about this AD, 

contact Andrew McAnaul, Aerospace 

Engineer, ASW–150 (c/o MIDO–43), 10100 

Reunion Place, Suite 650, San Antonio, 

Texas 78216; phone: (210) 308–3365; fax: 

(210) 308–3370; email: andrew.mcanaul@

faa.gov. 

(2) For service information identified in 

this AD, contact Air Tractor, Inc., P.O. Box 

485, Olney, Texas 76374; telephone: (940) 

564–5616; fax: (940) 564–5612; email: 

airmail@airtractor.com; Internet: 

www.airtractor.com. You may review copies 

of the referenced service information at the 

FAA, Small Airplane Directorate, 901 Locust, 

Kansas City, Missouri 64106. For information 

on the availability of this material at the 

FAA, call 816–329–4148. 

Issued in Kansas City, Missouri, on 

February 5, 2014. 

Earl Lawrence, 

Manager, Small Airplane Directorate, Aircraft 

Certification Service. 

[FR Doc. 2014–03024 Filed 2–11–14; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2014–0070; Directorate 

Identifier 2011–SW–062–AD] 

RIN 2120–AA64 

Airworthiness Directives; Bell 

Helicopter Textron Canada Helicopters 

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 407 helicopters. This proposed 

AD would require inspecting the aft 

fuselage upper skin (upper skin) for a 

crack and the upper left longeron 

assembly (longeron assembly) for a 

crack, corrosion, or defect. This AD 

would require replacing or repairing a 

part or section, depending on the 

inspection’s outcome. This proposed 

AD is prompted by reports of cracks in 

the upper left-hand longeron. The 

proposed actions are intended to 

prevent failure of the longeron assembly 

or the upper skin, which could lead to 

a structural failure and loss of helicopter 

control. 

DATES: We must receive comments on 

this proposed AD by April 14, 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 

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: 

Sharon Miles, Aviation Safety Engineer, 

Regulations and Policy Group, 

Rotorcraft Directorate, FAA, 2601 

Meacham Blvd., Fort Worth, Texas 

76137; telephone (817) 222–5110; email 

sharon.y.miles@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–2011–42, dated November 9, 2011, 

to correct an unsafe condition for 

certain BHTC Model 407 helicopters. 

TCCA advises that longeron assemblies, 

part numbers (P/Ns) 206–031–314–037, 

206–031–314–177, and 206–031–314– 

219B, installed on helicopters with 


tkelley on DSK3SPTVN1PROD with PROPOSALS
Federal Register / Vol. 79, No. 29 / Wednesday, February 12, 2014 / Proposed Rules 8359 

1,200 or more hours air time, are prone 

to cracking. The TCCA AD requires, 

based on hours air time since new, 

visually inspecting the aft fuselage 

upper skin for cracks and replacing the 

skin if cracked. The TCCA AD also 

requires visually inspecting the 

longeron assembly for cracks and 

general condition. If the longeron 

assembly is serviceable, the TCCA AD 

requires repeating the inspection of the 

longeron assembly for cracks and 

general condition at intervals based on 

whether external strap doublers are 

installed. If the longeron assembly is 

cracked, the TCCA AD requires 

repairing or replacing it, installing three 

external strap doublers, and repeating 

the inspection of the longeron assembly 

if it was repaired. Installing a new 

longeron assembly, P/N 206–031–314– 

237B, and the three external strap 

doublers constitutes terminating action 

of the TCCA 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, the 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 

BHTC has issued Alert Service 

Bulletin 407–11–95, Revision C, dated 

April 20, 2012 (ASB), to correct an 

unsafe condition for Model 407 

helicopters, serial numbers 53000 

through 53900, 53911 through 54061, 

and 54300, with a flight time of 1200 or 

more hours, and with a longeron 

assembly, P/N 206–031–314–037, 206– 

031–314–177, or 206–031–314–219B. 

The ASB states that BHTC received 

reports of longeron assemblies cracking 

in service. The ASB: 

• Specifies a one-time inspection of 

the aft fuselage top skin and repetitive 

inspections of the upper left longeron 

assembly; 

• Provides a repair procedure for the 

longeron assembly; 

• Allows for the installation of 

longeron assembly, P/N 206–031–314– 

237B, and three external strap doublers 

as terminating action for the repetitive 

inspection requirements. 

Proposed AD Requirements 

We propose the following: 

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

or prior to reaching 1,250 hours TIS 

since new, whichever occurs later, 

visually inspect the upper skin for a 

crack using a 10X or higher power 

magnifying glass. 

• If there is a crack in the upper skin, 

before further flight, remove the skin 

and inspect the longeron assembly, 

paying attention to the upper flange, for 

a crack, corrosion, or other damage 

using a 10X or higher power magnifying 

glass. If there are no cracks, corrosion, 

or other damage in the longeron 

assembly, before further flight, replace 

the upper skin with an airworthy upper 

skin. Repeat the inspection of the 

longeron assembly at intervals not to 

exceed 50 hours TIS. If there is a crack, 

corrosion, or other damage in the 

longeron assembly, before further flight: 

Repair the longeron assembly or replace 

it with an airworthy longeron assembly, 

P/N 206–031–314–237B, and reinstall 

the upper skin or replace it with an 

airworthy upper skin. Install three 

external strap doublers. Repeat the 

inspection of the longeron assembly at 

intervals not to exceed 50 hours TIS. 

• If there is no crack in the upper 

skin, within 10 hours TIS, visually 

inspect the longeron assembly using a 

10X or higher power magnifying glass 

for a crack, corrosion, or other damage. 

If there is a crack, corrosion, or other 

damage in the longeron assembly, before 

further flight: Repair the longeron 

assembly or replace it with an airworthy 

longeron assembly, P/N 206–031–314– 

237B. Install three external strap 

doublers. Repeat the inspection of the 

upper skin and longeron assembly at 

intervals not to exceed 50 hours TIS. If 

there are no cracks, corrosion, or other 

damage in the longeron assembly, repeat 

the inspection of the upper skin and 

longeron assembly at intervals not to 

exceed 50 hours TIS. 

• Replacing the longeron assembly 

with longeron assembly, P/N 206–031– 

314–237B, and installing three external 

strap doublers constitutes terminating 

action for this AD. If there is no crack 

in the upper skin and no crack, 

corrosion or other damage in the 

longeron assembly, you may install 

three external strap doublers, which 

will extend the recurring 50 hours TIS 

inspection interval to 150 hours TIS. 

Costs of Compliance 

We estimate that this proposed AD 

would affect 584 helicopters of U.S. 

Registry and that labor costs average $85 

an hour. Based on these estimates, we 

estimate the following costs: 

A one-time visual inspection of the aft 

fuselage upper skin would require 1 

work-hour and no parts for a total cost 

of $85 per helicopter, $49,640 for the 

U.S. fleet. 

A visual inspection of the longeron 

and replacing the aft fuselage upper skin 

would require 3 work hours for a labor 

cost of $255 per helicopter. Parts would 

cost $723 for parts for total cost of $978 

per helicopter. 

Repairing the longeron if needed and 

installing the doublers would require 16 

work hours for a labor cost of $1,360. 

Parts would cost $3,928 for a total cost 

of $5,288 per helicopter. 

Replacing the longeron with P/N 206– 

031–314–237B combined with the 

installation of the three external strap 

doublers would require 24 work hours 

for a labor cost of $2,040. Parts would 

cost $13,560 for a total cost of $15,600 

per helicopter. 

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 

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, 


tkelley on DSK3SPTVN1PROD with PROPOSALS
8360 Federal Register / Vol. 79, No. 29 / Wednesday, February 12, 2014 / Proposed Rules 

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. The FAA amends § 39.13 by adding 

the following new airworthiness 

directive (AD): 

Bell Helicopter Textron Canada: Docket No. 

FAA–2014–0070; Directorate Identifier 

2011–SW–062–AD. 

(a) Applicability 

This AD applies to Bell Helicopter Textron 

Canada (BHTC) Model 407 helicopters, with 

a serial number 53000 through 53900, 53911 

through 54061, and 54300, with an upper left 

longeron assembly (longeron assembly), part 

number (P/N) 206–031–314–037, 206–031– 

314–177, or 206–031–314–219B, installed, 

certificated in any category. 

(b) Unsafe Condition 

This AD defines the unsafe condition as a 

crack in the aft fuselage upper skin or a 

crack, corrosion, or defect in the longeron 

assembly. This condition could cause 

structural failure and consequently, loss of 

helicopter control. 

(c) Comments Due Date 

We must receive comments by April 14, 

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 

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

prior to reaching 1,250 hours TIS since new, 

whichever occurs later, visually inspect the 

helicopter’s aft fuselage upper skin (upper 

skin) for a crack using a 10X or higher power 

magnifying glass. 

(1) If there is a crack in the upper skin, 

before further flight, remove the skin and 

inspect the longeron assembly, paying 

attention to the upper flange, for a crack, 

corrosion, or other damage using a 10X or 

higher power magnifying glass. 

(i) If there are no cracks, corrosion, or other 

damage in the longeron assembly, before 

further flight, replace the upper skin with an 

airworthy upper skin. Repeat the inspection 

of the longeron assembly at intervals not to 

exceed 50 hours TIS. 

(ii) If there is a crack, corrosion, or other 

damage in the longeron assembly, before 

further flight: 

(A) Repair the longeron assembly or 

replace it with an airworthy longeron 

assembly, part number (P/N) 206–031–314– 

237B, and reinstall the upper skin or replace 

it with an airworthy upper skin. 

(B) Install three external strap doublers in 

accordance with Part III, paragraphs 5 

through10 of Bell Alert Service Bulletin 407– 

11–95, Revision C, dated April 20, 2012 

(ASB). 

(C) Repeat the inspection of the longeron 

assembly at intervals not to exceed 50 hours 

TIS. 

(2) If there is no crack in the upper skin, 

within 10 hours TIS, visually inspect the 

longeron assembly using a 10X or higher 

power magnifying glass for a crack, 

corrosion, or other damage. 

(i) If there is a crack, corrosion, or other 

damage in the longeron assembly, before 

further flight: 

(A) Repair the longeron assembly or 

replace it with an airworthy longeron 

assembly, P/N 206–031–314–237B. 

(B) Install three external strap doublers in 

accordance with Part III, paragraphs 5 

through 10 of the ASB. 

(C) Repeat the inspection of the upper skin 

and longeron assembly at intervals not to 

exceed 50 hours TIS. 

(ii) If there are no cracks, corrosion, or 

other damage in the longeron assembly, 

repeat the inspection of the upper skin and 

longeron assembly at intervals not to exceed 

50 hours TIS. 

(3) Replacing the longeron assembly with 

longeron assembly, P/N 206–031–314–237B, 

and installing three external strap doublers 

constitutes terminating action for this AD. 

(4) If there is no crack in the upper skin 

and there is no crack, corrosion, or other 

damage in the longeron assembly, you may 

install three external strap doublers in 

accordance with Part III, paragraphs 5 

through 10 of the ASB. This option extends 

the recurring 50 hours TIS inspection 

interval to 150 hours TIS. 

(f) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Safety Management 

Group, FAA, may approve AMOCs for this 

AD. Send your proposal to: Sharon Miles, 

Aviation Safety Engineer, Regulations and 

Policy Group, Rotorcraft Directorate, FAA, 

2601 Meacham Blvd., Fort Worth, Texas 

76137; telephone (817) 222–5110; email 

sharon.y.miles@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 Civil Aviation (TCCA) AD 

No. CF–2011–42, dated November 9, 2011. 

You may view the TCCA AD in the AD 

docket on the Internet at 

http://www.regulations.gov. 

(h) Subject 

Joint Aircraft Service Component (JASC) 

Code: 5313, Fuselage Main, Longeron/

Stringer. 

Issued in Fort Worth, Texas, on January 31, 

2014. 

Lance T. Gant, 

Acting Directorate Manager, Rotorcraft 

Directorate, Aircraft Certification Service. 

[FR Doc. 2014–02954 Filed 2–11–14; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 71 

[Docket No. FAA–2013–0806; Airspace 

Docket No. 13–ASO–21] 

Proposed Amendment of Class D and 

Class E Airspace, and Proposed 

Establishment of Class E Airspace; TriCities, TN 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: This action proposes to 

amend Class D and Class E Airspace, 

and establish Class E airspace at TriCities Regional Airport, Tri-Cities, TN. 

Airspace reconfiguration would 

alleviate traffic issues in the 

surrounding area for Johnson City 

Airport and Edwards Heliport so flights 

could navigate in and out of their 

respective airports in Visual Flight 

Rules conditions under 700 feet. This 

would enhance the safety and airspace 

management of Instrument Flight Rules 

(IFR) operations in the area. 

DATES: Comments must be received on 

or before March 31, 2014. 

ADDRESSES: Send comments on this rule 

to: U.S. Department of Transportation, 

Docket Operations, West Building 

Ground Floor, Room W12–140, 1200 

New Jersey SE., Washington, DC 20590– 

0001; Telephone: 1–800–647–5527; Fax: 

202–493–2251. You must identify the 

Docket Number FAA–2013–0806; 

Airspace Docket No. 13–ASO–21, at the 

beginning of your comments. You may 

also submit and review received 


tkelley on DSK3SPTVN1PROD with PROPOSALS