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
Federal Register / Vol. 78, No. 211 / Thursday, October 31, 2013 / Rules and Regulations 65205 

FOR FURTHER INFORMATION CONTACT: 

Todd Thompson, Aerospace Engineer, 

International Branch, ANM–116, 

Transport Airplane Directorate, FAA, 

1601 Lind Avenue SW., Renton, WA 

98057–3356; telephone: (425) 227–1175; 

fax (425) 227–1149. 

SUPPLEMENTARY INFORMATION:

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 by adding an AD that would 

apply to the specified products. The 

NPRM published in the Federal 

Register on July 31, 2013 (78 FR 46301). 

The NPRM proposed to correct an 

unsafe condition for the specified 

products. 

The European Aviation Safety Agency 

(EASA), which is the Technical Agent 

for the Member States of the European 

Community, has issued EASA 

Airworthiness Directive 2012–0136, 

dated July 20, 2012 (referred to after this 

as the Mandatory Continuing 

Airworthiness Information, or ‘‘the 

MCAI’’), to correct an unsafe condition 

for the specified products. The MCAI 

states: 

While carrying out a scheduled 

environmental inspection, an operator found 

a cracked number 1 engine forward outboard 

pylon pick-up bracket. Cracks were present 

on the upper flange of the bracket running 

between all 3 attachment bolt holes. 

Subsequent investigation revealed that the 

cause of cracking was stress corrosion. 

Cracking of the pylon pick-up brackets at the 

top and bottom flanges could reduce the 

capability of the brackets to support the 

ultimate sideload, particularly if cracking is 

present on more than one flange. 

This condition, if not detected and 

corrected, could result in the engine pylon 

separation from the wing, likely resulting in 

damage to [and controllability of] the 

aeroplane and possible injury to persons on 

the ground. 

* * * * * 

For reasons described above, this [EASA] 

AD requires the inspection and, depending 

on findings, repair of the affected pylon pickup brackets. 

The inspection includes a special 

detailed inspection with a videoscope. 

Corrective actions can include replacing 

any affected pylon pick-up brackets, and 

doing any follow-on skin repairs. You 

may examine the MCAI in the AD 

docket on the Internet at http://

www.regulations.gov/

#!documentDetail;D=FAA-2013-0631- 

0002. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. We 

received no comments on the NPRM (78 

FR 46301, July 31, 2013) or on the 

determination of the cost to the public. 

Conclusion 

We reviewed the available data and 

determined that air safety and the 

public interest require adopting this AD 

as proposed—except for minor editorial 

changes. We have determined that these 

minor changes: 

• Are consistent with the intent that 

was proposed in the NPRM (78 FR 

46301, July 31, 2013) for correcting the 

unsafe condition; and 

• Do not add any additional burden 

upon the public than was already 

proposed in the NPRM (78 FR 46301, 

July 31, 2013). 

Costs of Compliance 

Based on the service information, we 

estimate that this AD affects 1 product 

of U.S. registry. We also estimate that it 

takes 2 work-hours per product to 

comply with the basic requirements of 

this AD. The average labor rate is $85 

per work-hour. Based on these figures, 

we estimate the cost of this AD on U.S. 

operators to be $170, or $170 per 

product. 

We have received no definitive data 

that would enable us to provide cost 

estimates for the on-condition actions 

specified in this AD. 

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 above, I 

certify that this AD: 

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; 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 a regulatory evaluation 

of the estimated costs to comply with 

this AD and placed it in the AD docket. 

Examining the AD Docket 

You may examine the MCAI in the 

AD docket on the Internet at http://

www.regulations.gov/

#!documentDetail;D=FAA-2013-0631- 

0002; 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 MCAI, the 

regulatory evaluation, any comments 

received, and other information. The 

street address for the Docket Operations 

office (telephone (800) 647–5527) is in 

the ADDRESSES section. 

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 AD: 

2013–22–08 BAE Systems (Operations) 

Limited: Amendment 39–17640. Docket 

No. FAA–2013–0631; Directorate 

Identifier 2012–NM–142–AD. 

(a) Effective Date 

This airworthiness directive (AD) becomes 

effective December 5, 2013. 

(b) Affected ADs 

None. 


wreier-aviles on DSK5TPTVN1PROD with RULES
65206 Federal Register / Vol. 78, No. 211 / Thursday, October 31, 2013 / Rules and Regulations 

(c) Applicability 

This AD applies to BAE Systems 

(Operations) Limited Model BAe 146–100A, 

–200A, and –300A airplanes; and Model 

Avro 146–RJ70A, 146–RJ85A, and 146– 

RJ100A airplanes; certificated in any 

category, all serial numbers. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 57, Wings. 

(e) Reason 

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. 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. 

(f) Compliance 

You are responsible for having the actions 

required by this AD performed within the 

compliance times specified, unless the 

actions have already been done. 

(g) Repetitive Inspections 

(1) Within the initial compliance time 

specified in paragraphs (g)(1)(i) and (g)(1)(ii) 

of this AD, as applicable, and thereafter at 

intervals not to exceed 24 months: Do a 

special detailed inspection with a videoscope 

of the flanges of the Rib 10 forward pylon 

pick-up bracket of each engine pylon for 

cracking, corrosion, and other defects, in 

accordance with the Accomplishment 

Instructions of BAE Systems (Operations) 

Limited Inspection Service Bulletin ISB.57– 

073, Revision 1, dated January 27, 2012; or 

Revision 2, dated March 8, 2012. 

(i) Within 6 months after the effective date 

of this AD, except as provided by paragraph 

(g)(1)(ii) of this AD. 

(ii) For airplanes on which a maintenance 

records check positively determines that both 

forward pylon pick-up brackets have been 

replaced since first flight of the airplane: 

Within 20 months after the effective date of 

this AD. 

(2) If, during any inspection required by 

paragraph (g)(1) of this AD, any cracking, 

corrosion or other defect of any Rib 10 

forward pylon pick-up bracket is found: 

Before further flight, repair or replace the 

bracket as specified in paragraph (g)(2)(i) or 

(g)(2)(ii) of this AD. 

(i) Repair a bracket in accordance with the 

Accomplishment Instructions of BAE 

Systems (Operations) Limited Inspection 

Service Bulletin ISB.57–073, Revision 1, 

dated January 27, 2012; or Revision 2, dated 

March 8, 2012. 

(ii) Replace a bracket using a method 

approved by either the Manager, 

International Branch, ANM–116, Transport 

Airplane Directorate, FAA; or the European 

Aviation Safety Agency (EASA) (or its 

delegated agent). 

(3) Repairing or replacing a Rib 10 forward 

pylon pick-up bracket, as required by 

paragraph (g)(2) of this AD, does not 

terminate the repetitive inspections required 

by paragraph (g)(1) of this AD. 

(h) Credit for Previous Actions 

This paragraph provides credit for actions 

required by paragraph (g) of this AD, if the 

actions were performed before the effective 

date of this AD using BAE Systems 

(Operations) Limited Inspection Service 

Bulletin ISB.57–073, dated September 6, 

2010, which is not incorporated by reference 

in this AD. 

(i) 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: 

Todd Thompson, Aerospace Engineer, 

International Branch, ANM–116, Transport 

Airplane Directorate, FAA, 1601 Lind 

Avenue SW., Renton, WA 98057–3356; 

telephone (425) 227–1175; fax (425) 227– 

1149. Information may be emailed to: 9- 

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

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. 

(2) Airworthy Product: For any requirement 

in this AD to obtain corrective actions from 

a manufacturer or other source, use these 

actions if they are FAA-approved. Corrective 

actions are considered FAA-approved if they 

are approved by the State of Design Authority 

(or their delegated agent). You are required 

to assure the product is airworthy before it 

is returned to service. 

(j) Related Information 

(1) Refer to Mandatory Continuing 

Airworthiness Information (MCAI) European 

Aviation Safety Agency Airworthiness 

Directive 2012–0136, dated July 20, 2012, for 

related information. You may examine the 

MCAI in the AD docket on the Internet at 

http://www.regulations.gov/

#!documentDetail;D=FAA-2013-0631-0002. 

(2) Service information identified in this 

AD that is not incorporated by reference may 

be obtained at the addresses specified in 

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

(k) 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 this AD specifies otherwise. 

(i) BAE Systems (Operations) Limited 

Inspection Service Bulletin ISB.57–073, 

Revision 1, dated January 27, 2012. 

(ii) BAE Systems (Operations) Limited 

Inspection Service Bulletin ISB.57–073, 

Revision 2, dated March 8, 2012. 

(3) 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. 

(4) You may review copies of the 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. 

(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 

17, 2013. 

Jeffrey E. Duven, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2013–25627 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–2013–0491; Directorate 

Identifier 2008–SW–012–AD; Amendment 

39–17609; AD 2013–20–03] 

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 certain 

Bell Model 430 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. 


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