Federal Register / Vol. 78, No. 6 / Wednesday, January 9, 2013 / Rules and Regulations 1731 

for the power cable assembly 

replacement kit. Based on these figures, 

the cost of the AD on U.S. operators will 

be $13,504 per helicopter, or $418,624 

for the 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 

products 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. 

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): 

2012–26–11 Bell Helicopter Textron Inc.: 

Amendment 39–17306; Docket No. 

FAA–2012–0601; Directorate Identifier 

2008–SW–033–AD. 

(a) Applicability 

This AD applies to Bell Helicopter Textron 

Inc. (BHTI) Model 205A, 205A–1, and 205B 

helicopters with starter/generator power 

cable assemblies (power cable assemblies), 

part number (P/N) 205–075–902–017 and P/ 

N 205–075–911–007 installed, certificated in 

any category. 

(b) Unsafe Condition 

This AD defines the unsafe condition as 

the power cable assembly connector 

(connector) deterioration, which can cause a 

short in the connector potentially leading to 

a fire in the starter/generator. A fire would 

result in smoke in the cockpit, reducing 

visibility, and risking loss of control of the 

helicopter. 

(c) Effective Date 

This AD becomes effective February 13, 

2013. 

(d) Compliance 

You are responsible for performing each 

action required by this AD within the 

specified compliance time unless 

accomplished previously. 

(e) Required Actions 

Within six months, replace the power cable 

assemblies using the parts contained in 

starter/generator kit P/N CT205–07–94–1, 

perform a continuity test, and connect wires 

to the starter generator as follows: 

(1) For Model 205A and 205A–1 

helicopters, follow the Accomplishment 

Instructions, paragraphs 2 through 16(c), of 

BHTI Alert Service Bulletin No. 205–07–94, 

Revision A, dated December 8, 2008. 

(2) For the Model 205B helicopters, follow 

the Accomplishment Instructions, paragraphs 

2 through 16(c), of BHTI Alert Service 

Bulletin No. 205B–08–50, dated December 8, 

2008. 

(f) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Safety Management 

Group, FAA, may approve AMOCs for this 

AD. Send your proposal to: Andy Shaw, 

Aviation Safety Engineer, Safety Management 

Group, Rotorcraft Directorate, FAA, 2601 

Meacham Blvd., Fort Worth, TX 76137; 

telephone (817) 222–5110; email 

andy.shaw@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) Subject 

Joint Aircraft Service Component (JASC) 

Code: 2497, electrical power system wiring. 

(h) 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) Bell Helicopter Textron Inc. Alert 

Service Bulletin No. 205–07–94, Revision A, 

dated December 8, 2008. 

(ii) Bell Helicopter Textron Inc. Alert 

Service Bulletin No. 205B–08–50, dated 

December 8, 2008. 

(3) For Bell Helicopter Textron Inc. service 

information identified in this AD, contact 

Bell Helicopter Textron, Inc., P.O. Box 482, 

Fort Worth, TX 76101; telephone (817) 280– 

3391; fax (817) 280–6466; 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/ 

index.html. 

Issued in Fort Worth, Texas, on December 

20, 2012. 

Kim Smith, 

Directorate Manager, Rotorcraft Directorate, 

Aircraft Certification Service. 

[FR Doc. 2012–31586 Filed 1–8–13; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2012–1032; Directorate 

Identifier 2012–NM–079–AD; Amendment 

39–17296; AD 2012–26–01] 

RIN 2120–AA64 

Airworthiness Directives; Saab AB, 

Saab Aerosystems Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 


srobinson on DSK4SPTVN1PROD with 
1732 Federal Register / Vol. 78, No. 6 / Wednesday, January 9, 2013 / Rules and Regulations 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for all Saab 

AB, Saab Aerosystems Model SAAB 

2000 airplanes. This AD was prompted 

by reports of chafing on the bottom 

panel of the center cabin. This AD 

requires a general visual inspection to 

determine if certain fasteners are 

installed, and related investigative and 

corrective actions. We are issuing this 

AD to detect and correct any chafing on 

the bottom panel of the center cabin, 

which could affect the structural 

integrity of the affected wing-to-fuselage 

connection. 

DATES: This AD becomes effective 

February 13, 2013. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of February 13, 2013. 

ADDRESSES: You may examine the AD 

docket on the Internet at http:// 

www.regulations.gov 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 FURTHER INFORMATION CONTACT: 

Shahram Daneshmandi, Aerospace 

Engineer, International Branch, ANM– 

116, Transport Airplane Directorate, 

FAA, 1601 Lind Avenue SW., Renton, 

WA 98057–3356; telephone 425–227– 

1112; fax 425–227–1149. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to include an AD that would 

apply to the specified products. That 

NPRM was published in the Federal 

Register on October 2, 2012 (77 FR 

60073). That NPRM proposed to correct 

an unsafe condition for the specified 

products. The Mandatory Continuing 

Airworthiness Information (MCAI) 

states: 

On two SAAB 2000 aeroplanes, signs of 

chafing have been found on the bottom panel 

of the centre cabin between fuselage station 

(STA) 562 and STA 622. The investigation 

results have shown that the chafing is caused 

by certain Hi Lok fasteners, installed as a 

repair during production, through the upper 

wing skin panel. 

This condition, if not detected and 

corrected, could affect the structural integrity 

of the affected wing-to-fuselage connection. 

To address this potential unsafe condition, 

SAAB issued Service Bulletin (SB) 2000–53– 

057 to provide instructions for a general 

visual inspection to detect chafing in the area 

between the upper wing skin and the cabin 

centre bottom panel and to verify if there are 

Hi Lok fasteners installed with the collar up. 

For the reasons described above, this 

[European Aviation Safety Agency (EASA)] 

AD requires a one-time inspection of the 

designated area, the accomplishment of 

corrective action(s) [repair], depending on 

findings, and the reporting of all inspection 

results * * *. 

This [EASA] AD is considered an interim 

action and further AD action may follow. 

Related investigative actions include 

measuring the distance between the 

fastener and bottom panel and a 

boroscope inspection for chafing and 

damage of the bottom panel. You may 

obtain further information by examining 

the MCAI in the AD docket. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. We 

received no comments on the NPRM (77 

FR 60073, October 2, 2012) 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 the AD 

as proposed. 

Costs of Compliance 

We estimate that this AD will affect 

10 products of U.S. registry. We also 

estimate that it will take about 4 workhours 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 to the U.S. operators to 

be $3,400, or $340 per product. 

We have received no definitive data 

that would enable us to provide a cost 

estimate 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 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 the NPRM (77 FR 60073, 

October 2, 2012), 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. Comments will be available in 

the AD docket shortly after receipt. 

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: 

2012–26–01 Saab AB, Saab Aerosystems: 

Amendment 39–17296. Docket No. 

FAA–2012–1032; Directorate Identifier 

2012–NM–079–AD. 


srobinson on DSK4SPTVN1PROD with 
Federal Register / Vol. 78, No. 6 / Wednesday, January 9, 2013 / Rules and Regulations 1733 

(a) Effective Date 

This airworthiness directive (AD) becomes 

effective February 13, 2013. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to Saab AB, Saab 

Aerosystems Model SAAB 2000 airplanes, 

certificated in any category, all serial 

numbers. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 53, Fuselage. 

(e) Reason 

This AD was prompted by reports of 

chafing on the bottom panel of the center 

cabin. We are issuing this AD to detect and 

correct any chafing on the bottom panel of 

the center cabin, which could affect the 

structural integrity of the affected wing-tofuselage connection. 

(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) Inspection 

Within 12 months after the effective date 

of this AD, do a general visual inspection of 

the area between the upper part of the wing 

skin and the center bottom panel to 

determine if any Hi Lok fasteners are 

installed with the collar up, and do all 

applicable related investigative actions, in 

accordance with the Accomplishment 

Instructions of Saab Service Bulletin 2000– 

53–057, dated November 22, 2011. 

(h) Repair 

If any chafing or damage is found during 

any inspection required by paragraph (g) of 

this AD: Before further flight, repair in 

accordance with a method approved by the 

Manager, International Branch, ANM–116, 

Transport Airplane Directorate, FAA; or the 

European Aviation Safety Agency (EASA) (or 

its delegated agent). 

(i) Reporting 

Submit a report of the findings (both 

positive and negative) of the inspection 

required by paragraph (g) of this AD to Saab 

AB, Saab Aerosystems, in accordance with 

the Accomplishment Instructions of Saab 

Service Bulletin 2000–53–057, dated 

November 22, 2011, at the applicable time 

specified in paragraph (i)(1) or (i)(2) of this 

AD. The report must include the inspection 

results, the airplane serial number, and the 

number of landings and flight hours on the 

airplane. 

(1) If the inspection was done on or after 

the effective date of this AD: Submit the 

report within 30 days after the inspection. 

(2) If the inspection was done before the 

effective date of this AD: Submit the report 

within 30 days after the effective date 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: 

Shahram Daneshmandi, Aerospace Engineer, 

International Branch, ANM–116, Transport 

Airplane Directorate, FAA, 1601 Lind 

Avenue SW., Renton, WA 98057–3356; 

telephone 425–227–1112; 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. 

(3) Reporting Requirements: A federal 

agency may not conduct or sponsor, and a 

person is not required to respond to, nor 

shall a person be subject to a penalty for 

failure to comply with a collection of 

information subject to the 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. 

(k) Related Information 

Refer to MCAI EASA Airworthiness 

Directive 2012–0068, dated April 25, 2012; 

and Saab Service Bulletin 2000–53–057, 

dated November 22, 2011; for related 

information. 

(l) 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) Saab Service Bulletin 2000–53–057, 

dated November 22, 2011. 

(ii) Reserved. 

(3) For service information identified in 

this AD, contact Saab AB, Saab Aeronautics, 

SE–581 88, Linko ̈ping, Sweden; telephone 

+46 13 18 5591; fax +46 13 18 4874; email 

saab2000.techsupport@saabgroup.com; 

Internet http://www.saabgroup.com. 

(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 

December 14, 2012. 

Kalene C. Yanamura, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2012–31035 Filed 1–8–13; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2010–0820; Directorate 

Identifier 2010–NE–31–AD; Amendment 39– 

17308; AD 2012–26–13] 

RIN 2120–AA64 

Airworthiness Directives; Thielert 

Aircraft Engines GmbH Reciprocating 

Engines 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are superseding an 

existing airworthiness directive (AD) for 

all Thielert Aircraft Engines GmbH 

models TAE 125–01, TAE 125–02–99, 

and TAE 125–02–114 reciprocating 

engines. That AD currently requires 

installation of full-authority digital 

electronic control (FADEC) software 

version 2.91. This new AD requires 

removing all software mapping versions 

prior to 292, 301, or 302, applicable to 

the TAE engine model. This AD was 

prompted by reports of possible power 

loss on airplanes equipped with TAE 

125 engines. We are issuing this AD to 

prevent engine power loss or in-flight 

shutdown, resulting in reduced control 

of or damage to the airplane. 

DATES: This AD is effective February 13, 

2013. 

ADDRESSES: For service information 

identified in this AD, contact Thielert 


srobinson on DSK4SPTVN1PROD with