65202 Federal Register / Vol. 78, No. 211 / Thursday, October 31, 2013 / Rules and Regulations 

(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): 

2013–20–05 Bell Helicopter Textron 

Canada Limited (Bell): Amendment 39– 

17611; Docket No. FAA–2013–0490; 

Directorate Identifier 2008–SW–004–AD. 

(a) Applicability 

This AD applies to Bell Model 407 

helicopters, serial numbers 53000 through 

53644, certificated in any category. 

(b) Unsafe Condition 

This AD defines the unsafe condition as a 

third stage turbine vibration, which could 

result in turbine failure, engine power loss, 

and subsequent loss of control of the 

helicopter. 

(c) Effective Date 

This AD becomes effective December 5, 

2013. 

(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 30 days: 

(1) Revise the Operating Limitations 

section of the Model 407 Rotorcraft Flight 

Manual by inserting Section 1, Limitations, 

pages 1–6 and 1–14, of Bell BHT–407–FM– 

1, revision 3, dated April 26, 2005. 

(2) Remove placard part number (P/N) 

230–075–213–105, if installed. 

(3) Install placard P/N 230–075–213–111, 

or equivalent, directly below the NR/NP dual 

tachometer. 

(f) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Safety Management 

Group, FAA, may approve AMOCs for this 

AD. Send your proposal to: Chinh Vuong, 

Aviation Safety Engineer, Safety Management 

Group, Rotorcraft Directorate, FAA, 2601 

Meacham Blvd., Fort Worth, Texas 76137; 

telephone (817) 222–5110; email 

chinh.vuong@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 Alert Service Bulletin No. 407–05– 

67, dated June 8, 2005, 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 a copy of the 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 

Transport Canada Civil Aviation (TCCA) AD 

No. CF–2004–09R1, dated July 4, 2005. You 

may view the TCCA AD on the internet in 

the AD Docket at http://www.regulations.gov. 

(h) Subject 

Joint Aircraft Service Component (JASC) 

Code: 7250: Turbine Section. 

(i) 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) Pages 1–6 and 1–14 of Section 1, 

Limitations, of Bell Rotorcraft Flight Manual 

BHT–407–FM–1, Revision 3, dated April 26, 

2005. 

(ii) Reserved. 

(3) For Bell 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/. 

(4) You may view this service information 

at FAA, Office of the Regional Counsel, 

Southwest Region, 2601 Meacham Blvd., 

Room 663, Fort Worth, Texas 76137. 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 September 

20, 2013. 

Scott A. Horn, 

Acting Directorate Manager, Rotorcraft 

Directorate, Aircraft Certification Service. 

[FR Doc. 2013–24030 Filed 10–30–13; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2013–0492; Directorate 

Identifier 2008–SW–013–AD; Amendment 

39–17608; AD 2013–20–02] 

RIN 2120–AA64 

Airworthiness Directives; Bell 

Helicopter Textron Canada Limited 

(Bell) Helicopters 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for Bell 

Model 230 helicopters. This AD requires 

installing a placard on the instrument 

panel and revising the limitations 

section of the rotorcraft flight manual 

(RFM). This AD was prompted by 

several incidents of third stage engine 

turbine wheel failures, which were 

caused by excessive vibrations at certain 

engine speeds during steady-state 

operations. These actions are intended 

to alert pilots to avoid certain engine 

speeds during steady-state operations, 

prevent failure of the third stage engine 

turbine, engine power loss, and 

subsequent loss of control of the 

helicopter. 

DATES: This AD is effective December 5, 

2013. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain document listed in this AD 

as of December 5, 2013. 

ADDRESSES: 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, 

2601 Meacham Blvd., Room 663, Fort 

Worth, Texas 76137. 


wreier-aviles on DSK5TPTVN1PROD with RULES
Federal Register / Vol. 78, No. 211 / Thursday, October 31, 2013 / Rules and Regulations 65203 

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 AD, the foreign 

authority’s AD, any incorporated-byreference service information, the 

economic evaluation, any comments 

received, and other information. The 

street address for the Docket Operations 

Office (phone: 800–647–5527) is U.S. 

Department of Transportation, Docket 

Operations Office, M–30, West Building 

Ground Floor, Room W12–140, 1200 

New Jersey Avenue SE., Washington, 

DC 20590. 

FOR FURTHER INFORMATION CONTACT: 

Chinh Vuong, Aviation Safety Engineer, 

Safety Management Group, Rotorcraft 

Directorate, FAA, 2601 Meacham Blvd., 

Fort Worth, Texas 76137; telephone 

(817) 222–5110; email chinh.vuong@

faa.gov. 

SUPPLEMENTARY INFORMATION:

Discussion 

On June 7, 2013, at 78 FR 34279, the 

Federal Register published our notice of 

proposed rulemaking (NPRM), which 

proposed to amend 14 CFR part 39 by 

adding an AD that would apply to Bell 

Model 230 helicopters. The NPRM 

proposed to require installing a placard 

on the instrument panel and revising 

the Operating Limitations section of the 

Model 230 RFM to limit steady-state 

operation between speeds of 71% and 

92%. The proposed requirements were 

intended to alert pilots to avoid certain 

engine speeds during steady-state 

operations, prevent failure of the third 

stage engine turbine, engine power loss, 

and subsequent loss of control of the 

helicopter. 

The NPRM was prompted by AD No. 

CF–2005–24, dated July 4, 2005, issued 

by Transport Canada Civil Aviation 

(TCCA), which is the aviation authority 

for Canada. TCCA issued AD CF–2005– 

24 to correct an unsafe condition for 

Model 230 helicopters. TCCA advises of 

several failures of third stage turbine 

wheels used in Rolls Royce 250–C30S 

and 250–C47B engines and that three of 

these failures have occurred on the same 

engine used by Bell on Model 230 

helicopters. According to TCCA, Rolls 

Royce has determined that detrimental 

vibrations can occur within a particular 

range of turbine speeds, and may be a 

contributing factor to these failures. Bell 

has revised the operating limitations of 

the RFM and provided a corresponding 

decal on the instrument panel to inform 

pilots to avoid steady-state operations 

between 71% and 92% turbine speeds. 

The TCCA AD requires amending the 

RFM, advising pilots of the change, and 

installing a decal as described in Bell 

Alert Service Bulletin (ASB) No. 230– 

05–33, dated June 10, 2005 (ASB 230– 

05–33). 

Comments 

After our NPRM (78 FR 34279, June 

7, 2013) was published, we received 

comments from one commenter. 

Request 

Rolls-Royce Corporation requested 

that in addition to requiring the placard 

on the instrument panel, we allow 

operators the option to temporarily 

mark the Nr/Np gauge with colored tape, 

to provide a more visual aide to the 

pilot for the speed avoidance zone. 

We disagree. Marking the glass 

surface of the gauge can create parallax 

issues when viewing the avoidance 

ranges on the gauge, resulting in 

erroneous readings. 

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, reviewed the 

relevant information, considered the 

comment received, and determined the 

unsafe condition exists and is likely to 

exist or develop on other helicopters of 

the same type design 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 compliance 

within 10 calendar days, while this AD 

requires compliance within 30 days. 

Related Service Information 

Bell has issued ASB 230–05–33, 

which contains procedures for installing 

a placard on the instrument panel and 

for inserting the RFM changes into the 

flight manual. 

Costs of Compliance 

We estimate that this AD will affect 

12 helicopters of U.S. Registry. Based on 

an average labor rate of $85 per hour, we 

estimate that operators will incur the 

following costs in order to comply with 

this AD. Amending the RFM requires 

about 0.5 work-hour, for a cost per 

helicopter of about $43 and a cost to 

U.S. operators of $516. Installing the 

decal requires about 0.2 work-hour and 

required parts cost $20, for a cost per 

helicopter of $37 and a cost to U.S. 

operators of $444. Based on these 

estimates, the total cost of this AD will 

be $80 per helicopter and $960 for the 

U.S. operator fleet. 

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 

helicopters identified in this rulemaking 

action. 

Regulatory Findings 

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 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. 


wreier-aviles on DSK5TPTVN1PROD with RULES
65204 Federal Register / Vol. 78, No. 211 / Thursday, October 31, 2013 / Rules and Regulations 

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): 

2013–20–02 Bell Helicopter Textron 

Canada Limited (Bell): Amendment 39– 

17608; Docket No. FAA–2013–0492; 

Directorate Identifier 2008–SW–013–AD. 

(a) Applicability 

This AD applies to Bell Model 230 

helicopters, certificated in any category. 

(b) Unsafe Condition 

This AD defines the unsafe condition as a 

third stage turbine vibration, which could 

result in turbine failure, engine power loss, 

and subsequent loss of control of the 

helicopter. 

(c) Effective Date 

This AD becomes effective December 5, 

2013. 

(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 30 days: 

(1) Revise the Operating Limitations 

section of the Model 230 Rotorcraft Flight 

Manual by inserting Section 1, Limitations, 

page 1–12, of Bell BHT–230–FM–1, revision 

5, dated May 6, 2005. 

(2) Install placard part number 230–075– 

213–115, or equivalent, on the instrument 

panel directly below the No. 1 and No. 2 

engine oil temp/press indicator. 

(f) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Safety Management 

Group, FAA, may approve AMOCs for this 

AD. Send your proposal to: Chinh Vuong, 

Aviation Safety Engineer, Safety Management 

Group, Rotorcraft Directorate, FAA, 2601 

Meacham Blvd., Fort Worth, Texas 76137; 

telephone (817) 222–5110; email 

chinh.vuong@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 Alert Service Bulletin No. 230–05– 

33, dated June 10, 2005, 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 a copy of the 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 

Transport Canada Civil Aviation (TCCA) AD 

No. CF–2005–24, dated July 4, 2005. You 

may view the TCCA AD on the internet in 

the AD Docket at http://www.regulations.gov. 

(h) Subject 

Joint Aircraft Service Component (JASC) 

Code: 7250: Turbine Section. 

(i) 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) Page 1–12 of Section 1, Limitations, of 

Bell Rotorcraft Flight Manual BHT–230–FM– 

1, Revision 5, dated May 6, 2005. 

(ii) Reserved. 

(3) For Bell 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/. 

(4) You may view this service information 

at FAA, Office of the Regional Counsel, 

Southwest Region, 2601 Meacham Blvd., 

Room 663, Fort Worth, Texas 76137. 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 September 

19, 2013. 

Scott A. Horn, 

Acting Directorate Manager, Rotorcraft 

Directorate, Aircraft Certification Service. 

[FR Doc. 2013–24032 Filed 10–30–13; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2013–0631; Directorate 

Identifier 2012–NM–142–AD; Amendment 

39–17640; AD 2013–22–08] 

RIN 2120–AA64 

Airworthiness Directives; BAE 

Systems (Operations) Limited 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for all BAE 

Systems (Operations) Limited Model 

BAe 146 and Avro 146–RJ series 

airplanes. This AD was prompted by a 

report of a cracked pick-up bracket of 

the forward outboard pylon of the 

number 1 engine due to stress corrosion. 

This AD requires repetitive inspections 

and, depending on findings, repair of 

the pylon pick-up brackets. We are 

issuing this AD to detect and correct 

cracking of the pick-up bracket, which 

could result in the engine pylon 

separating from the wing, with 

consequent damage to the airplane and 

reduced controllability. 

DATES: This AD becomes effective 

December 5, 2013. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in this AD 

as of December 5, 2013. 

ADDRESSES: You may examine the AD 

docket on the Internet at http://

www.regulations.gov/

#!docketDetail;D=FAA-2013-0631; or in 

person at the U.S. Department of 

Transportation, Docket Operations, M– 

30, West Building Ground Floor, Room 

W12–140, 1200 New Jersey Avenue SE., 

Washington, DC. 

For service information identified in 

this AD, contact BAE Systems 

(Operations) Limited, Customer 

Information Department, Prestwick 

International Airport, Ayrshire, KA9 

2RW, Scotland, United Kingdom; 

telephone +44 1292 675207; fax +44 

1292 675704; email RApublications@

baesystems.com; Internet http://

www.baesystems.com/Businesses/

RegionalAircraft/index.htm. You may 

view this referenced 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. 


wreier-aviles on DSK5TPTVN1PROD with RULES