Federal Register / Vol. 80, No. 2 / Monday, January 5, 2015 / Rules and Regulations 153 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2013–0460; Directorate 

Identifier 2012–NM–222–AD; Amendment 

39–18054; AD 2014–26–03] 

RIN 2120–AA64 

Airworthiness Directives; Saab AB, 

Saab Aerosystems Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for all Saab 

AB, Saab Aerosystems Model 340B 

airplanes. This AD was prompted by a 

report that the elevator position quoted 

in an aircraft maintenance manual is 

incorrect and a report that the trunnion 

at the lower part of the control column 

was installed incorrectly. This AD 

requires an inspection of the stick 

pusher rigging and an inspection of the 

installation of the trunnion and the stick 

pusher rigging, and corrective actions if 

necessary. We are issuing this AD to 

correct the rigging of the elevator 

position of the stick pusher to reduce 

the probability of a negative effect on 

the handling quality during stall, which 

could result in reduced controllability 

of the airplane. 

DATES: This AD becomes effective 

February 9, 2015. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of February 9, 2015. 

ADDRESSES: You may examine the AD 

docket on the Internet at http://

www.regulations.gov/

#!docketDetail;D=FAA-2013-0460 or in 

person at the Docket Management 

Facility, 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 Saab AB, Saab 

Aeronautics, SE–581 88, Linko ̈ping, 

Sweden; telephone +46 13 18 5591; fax 

+46 13 18 4874; email 

saab340techsupport@saabgroup.com; 

Internet http://www.saabgroup.com. 

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. 

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 supplemental notice of 

proposed rulemaking (SNPRM) to 

amend 14 CFR part 39 by adding an AD 

that would apply to all Saab AB, Saab 

Aerosystems Model 340B airplanes. The 

SNPRM published in the Federal 

Register on August 12, 2014 (79 FR 

47025). We preceded the SNPRM with 

a notice of proposed rulemaking 

(NPRM) that published in the Federal 

Register on June 3, 2013 (78 FR 33010). 

The European Aviation Safety Agency 

(EASA), which is the Technical Agent 

for the Member States of the European 

Union, has issued EASA Airworthiness 

Directive 2013–0253, dated October 18, 

2013 (referred to after this as the 

Mandatory Continuing Airworthiness 

Information, or ‘‘the MCAI’’), to correct 

an unsafe condition on all Saab AB, 

Saab Aerosystems Model 340B 

airplanes. The MCAI states: 

The standard stick pusher maximum 

elevator position of a SAAB 340B, prior to 

delivery, is set at 7.5 degrees trailing edge 

down. It was recently discovered that this 

value has been incorrectly referenced in the 

SAAB 340B Aircraft Maintenance Manual 

(AMM), which quotes an elevator position of 

4 degrees trailing edge down for all 

aeroplanes, which is the correct value for 

SAAB SF340A aeroplanes only. 

If a SAAB 340B aeroplane has been rerigged in accordance with current AMM 

procedure, there is a possibility that the 

deflection of the elevator will be less than 

intended. 

This condition, if not corrected, will affect 

the stall characteristics on the outer part of 

the envelope at maximum flap setting and aft 

centre of gravity (CG) configuration, possibly 

resulting in reduced control of the aeroplane. 

To address this potential unsafe condition, 

SAAB AB Aeronautics issued Service 

Bulletin (SB) 340–27–105 to reduce the 

probability of a negative effect on the 

handling quality during stall. Consequently, 

EASA issued AD 2012–0256 [http://

www.regulations.gov/

#!documentDetail;D=FAA-2013-0460-0002] 

to require a one-time inspection of the stick 

pusher rigging and, depending on findings, 

adjustment to the correct setting. 

Since that [EASA] AD was issued, it has 

been reported that on some aeroplanes, 

during implementation of SB 340–27–105, 

the trunnion at the lower part of the control 

column was incorrectly installed. This 

prevents proper inspection of the stick 

pusher rigging. 

Prompted by this finding, SAAB issued SB 

340–27–115 with instructions for all 

aeroplanes, regardless whether SB 340–27– 

105 has been accomplished or not. 

For the reasons described above, this 

[EASA] AD retains the requirements of EASA 

AD 2012–0256, which is superseded, but 

requires the use of the improved and 

expanded instructions specified in SAAB SB 

340–27–115. 

You may examine the MCAI in the 

AD docket on the Internet at http://

www.regulations.gov/

#!documentDetail;D=FAA-2013-0460- 

0005. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. We 

received no comments on the SNPRM 

(79 FR 47025, August 12, 2014) or on 

the determination of the cost to the 

public. 

Conclusion 

We reviewed the relevant 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 SNPRM (79 FR 

47025, August 12, 2014) for correcting 

the unsafe condition; and 

• Do not add any additional burden 

upon the public than was already 

proposed in the SNPRM (79 FR 47025, 

August 12, 2014). 

Costs of Compliance 

We estimate that this AD affects 109 

airplanes of U.S. registry. 

We also estimate that it will take 

about 12 work-hours per product to 

comply with the basic requirements of 

this AD. The average labor rate is $85 

per work-hour. Required parts will cost 

about $10 per product. Based on these 

figures, we estimate the cost of this AD 

on U.S. operators to be $112,270, or 

$1,030 per product. 

Paperwork Reduction Act 

A federal agency may not conduct or 

sponsor, and a person is not required to 

respond to, nor shall a person be subject 

to 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 control 

number for the collection of information 

required by this AD is 2120–0056. The 

paperwork cost associated with this AD 

has been detailed in the Costs of 

Compliance section of this document 

and includes time for reviewing 

instructions, as well as completing and 

reviewing the collection of information. 

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154 Federal Register / Vol. 80, No. 2 / Monday, January 5, 2015 / Rules and Regulations 

Therefore, all reporting associated with 

this AD is 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. 

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. 

Examining the AD Docket 

You may examine the AD docket on 

the Internet at http://

www.regulations.gov/

#!docketDetail;D=FAA-2013-0460; or in 

person at the Docket Management 

Facility between 9 a.m. and 5 p.m., 

Monday through Friday, except Federal 

holidays. The AD docket contains this 

AD, 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 airworthiness 

directive (AD): 

2014–26–03 Saab AB, Saab Aerosystems: 

Amendment 39–18054. Docket No. 

FAA–2013–0460; Directorate Identifier 

2012–NM–222–AD. 

(a) Effective Date 

This AD becomes effective February 9, 

2015. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to Saab AB, Saab 

Aerosystems Model 340B airplanes, 

certificated in any category, all serial 

numbers. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 27, Flight controls. 

(e) Reason 

This AD was prompted by a report that the 

elevator position quoted in an aircraft 

maintenance manual is incorrect and a report 

that the trunnion at the lower part of the 

control column was installed incorrectly. We 

are issuing this AD to correct the rigging of 

the elevator position of the stick pusher to 

reduce the probability of a negative effect on 

the handling quality during stall, which 

could result in reduced controllability of the 

airplane. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Inspection 

Within 24 months after the effective date 

of this AD, do a detailed inspection of the 

installation of the trunnion at the lower part 

of the control column and the stick pusher 

rigging, in accordance with the 

Accomplishment Instructions of Saab Service 

Bulletin 340–27–115, dated July 19, 2013. 

(h) Corrective Actions 

If, during the inspection required by 

paragraph (g) of this AD, an incorrect setting 

of the stick pusher maximum elevator 

position is found, or if the trunnion at the 

lower part of the control column is installed 

incorrectly, before further flight, accomplish 

all applicable corrective actions, in 

accordance with the Accomplishment 

Instructions of Saab Service Bulletin 340–27– 

115, dated July 19, 2013; except where Saab 

Service Bulletin 340–27–115, dated July 19, 

2013, specifies to contact SAAB for 

corrective action, repair before further flight, 

using a method approved by the Manager, 

International Branch, ANM–116, Transport 

Airplane Directorate, FAA; or the European 

Aviation Safety Agency (EASA); or Saab AB, 

Saab Aerosystems’ EASA Design 

Organization Approval (DOA). If approved by 

the DOA, the approval must include the 

DOA-authorized signature. 

(i) Reporting Requirement 

After accomplishing corrective actions as 

required by paragraph (h) of this AD, record 

any incorrect rigging value that was detected 

and send a report to: Saab AB, Business Area 

Support and Services, Air Division, 

Technical Support, email: 

Saab340.techsupport@saabgroup.com; fax: 

+46 (0) 13 18 48 74; at the applicable time 

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

AD. 

(1) If the corrective action was done on or 

after the effective date of this AD: Submit the 

report within 30 days after accomplishing the 

corrective action. 

(2) If the corrective action 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, ANM–116, 

International Branch, 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) 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 

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Federal Register / Vol. 80, No. 2 / Monday, January 5, 2015 / Rules and Regulations 155 

by the Manager, International Branch, ANM– 

116, Transport Airplane Directorate, FAA; or 

EASA; or Saab AB, Saab Aerosystems’ EASA 

Design Organization Approval (DOA). If 

approved by the DOA, the approval must 

include the DOA-authorized signature. 

(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 Mandatory Continuing 

Airworthiness Information (MCAI) EASA 

Airworthiness Directive 2013–0253, dated 

October 18, 2013, for related information. 

This MCAI may be found in the AD docket 

on the Internet at http://

www.regulations.gov/

#!documentDetail;D=FAA-2013-0460-0005. 

(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 this AD specifies otherwise. 

(i) Saab Service Bulletin 340–27–115, 

dated July 19, 2013. 

(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 

saab340techsupport@saabgroup.com; 

Internet http://www.saabgroup.com. 

(4) 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. 

(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 17, 2014. 

Michael Kaszycki, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2014–30428 Filed 1–2–15; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2014–0848; Directorate 

Identifier 2014–CE–031–AD; Amendment 

39–18055; AD 2014–26–04] 

RIN 2120–AA64 

Airworthiness Directives; GROB– 

WERKE Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for certain 

GROB–WERKE Models G115EG and 

G120A airplanes. This AD results from 

mandatory continuing airworthiness 

information (MCAI) issued by an 

aviation authority of another country to 

identify and correct an unsafe condition 

on an aviation product. The MCAI 

describes the unsafe condition as a 

defective starter solenoid. We are 

issuing this AD to require actions to 

address the unsafe condition on these 

products. 

DATES: This AD is effective February 9, 

2015. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publication listed in the AD 

as of February 9, 2015. 

ADDRESSES: You may examine the AD 

docket on the Internet at http://

www.regulations.gov by searching for 

and locating Docket No. FAA–2014– 

0848; or in person at Document 

Management Facility, U.S. Department 

of Transportation, Docket Operations, 

M–30, West Building Ground Floor, 

Room W12–140, 1200 New Jersey 

Avenue SE., Washington, DC 20590. 

For service information identified in 

this AD, contact Grob Aircraft AG, 

Customer Service, Lettenbachstrasse 9, 

D–86874 Tussenhausen-Mattsies, 

Germany, telephone: + 49 (0) 8268–998– 

105; fax: + 49 (0) 8268–998–200; email: 

productsupport@grob-aircraft.com; 

Internet: grob-aircraft.com. You may 

view this 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. 

FOR FURTHER INFORMATION CONTACT: Karl 

Schletzbaum, Aerospace Engineer, FAA, 

Small Airplane Directorate, 901 Locust, 

Room 301, Kansas City, Missouri 64106; 

telephone: (816) 329–4123; fax: (816) 

329–4090; email: karl.schletzbaum@

faa.gov. 

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 certain GROB–WERKE Models 

G115EG and G120A airplanes. The 

NPRM was published in the Federal 

Register on October 23, 2014 (79 FR 

63340). The NPRM proposed to correct 

an unsafe condition for the specified 

products and was based on mandatory 

continuing airworthiness information 

(MCAI) originated by an aviation 

authority of another country. The MCAI 

states: 

An operator of a G 115E aeroplane 

experienced a total loss of electrical power in 

flight. The root cause was found to be a 

defective starter solenoid causing an internal 

short circuit, which resulted in breakdown of 

the system voltage. 

This condition, if not detected and 

corrected, could result in reduced control of 

the aeroplane. 

To address this potential unsafe condition, 

GROB Aircraft AG issued Service Bulletin 

(SB) MSB1078–196 for G 115 aeroplanes and 

SB MSB1121–144 for G 120 aeroplanes to 

provide instructions for inspection and 

corrective action. 

For the reason described above, this AD 

requires a one-time inspection of the starter 

solenoid and, depending on the findings, 

replacement of the starter. 

A technical solution is currently under 

development and further AD action may 

follow. 

The MCAI can be found in the AD 

docket on the Internet at http://

www.regulations.gov/

#!documentDetail;D=FAA-2014-0848- 

0002. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. We 

received no comments on the NPRM (79 

FR 63340, October 23, 2014) or on the 

determination of the cost to the public. 

Conclusion 

We reviewed the relevant data and 

determined that air safety and the 

public interest require adopting the AD 

as proposed except for minor editorial 

changes. We have determined that these 

minor changes: 

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