This section of the FEDERAL REGISTER

contains regulatory documents having general

applicability and legal effect, most of which

are keyed to and codified in the Code of

Federal Regulations, which is published under

50 titles pursuant to 44 U.S.C. 1510.

The Code of Federal Regulations is sold by

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REGISTER issue of each week.

Rules and Regulations Federal Register

76843 

Vol. 81, No. 214 

Friday, November 4, 2016 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2015–6544; Directorate 

Identifier 2014–NM–198–AD; Amendment 

39–18704; AD 2016–22–15] 

RIN 2120–AA64 

Airworthiness Directives; Saab AB, 

Saab Aeronautics (Formerly Known as 

Saab AB, Saab Aerosystems) 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: We are superseding 

Airworthiness Directive (AD) 2012–24– 

06 for certain Saab AB, Saab 

Aeronautics Model 340A (SAAB/ 

SF340A) and SAAB 340B airplanes. AD 

2012–24–06 required replacing the stall 

warning computer (SWC) with a new 

SWC that provides an artificial stall 

warning in icing conditions, and 

modifying the airplane for the 

replacement of the SWC. This new AD 

adds airplanes to the applicability, and 

adds requirements to replace the 

existing SWCs with new, improved 

SWCs, and to modify the airplane for 

the new replacement of the SWC. This 

new AD also reduces the compliance 

time for replacing the SWCs. This AD 

was prompted by a determination that 

airplanes with certain modifications 

were excluded from the applicability in 

AD 2012–24–06, and are affected by the 

identified unsafe condition; and that the 

SWC required by AD 2012–24–06 

contained erroneous logic. We are 

issuing this AD to prevent natural stall 

events during operation in icing 

conditions, which could result in loss of 

control of the airplane. 

DATES: This AD is effective December 9, 

2016. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in this AD 

as of December 9, 2016. 

ADDRESSES: For service information 

identified in this final rule, contact Saab 

AB, Saab Aeronautics, SE–581 88, 

Linko ̈ping, Sweden; telephone +46 13 

18 5591; fax +46 13 18 4874; email 

saab340.techsupport@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. It is also 

available on the Internet at http:// 

www.regulations.gov by searching for 

and locating Docket No. FAA–2015– 

6544. 

Examining the AD Docket 

You may examine the AD docket on 

the Internet at http:// 

www.regulations.gov by searching for 

and locating Docket No. FAA–2015– 

6544; 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 address for the 

Docket Office (telephone 800–647–5527) 

is 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 20590. 

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 to supersede AD 

2012–24–06, Amendment 39–17276 (77 

FR 73279, December 10, 2012) (‘‘AD 

2012–24–06’’). AD 2012–24–06 applied 

to certain Saab AB, Saab Aeronautics 

Model 340A (SAAB/SF340A) and SAAB 

340B airplanes. The SNPRM published 

in the Federal Register on July 12, 2016 

(81 FR 45072) (‘‘the SNPRM’’). We 

preceded the SNPRM with a notice of 

proposed rulemaking (NPRM) that 

published in the Federal Register on 

December 17, 2015 (80 FR 78699) (‘‘the 

NPRM’’). The NPRM was prompted by 

a determination that airplanes with 

certain modifications were excluded 

from the applicability in AD 2012–24– 

06, and are affected by the identified 

unsafe condition; and the SWC required 

by AD 2012–24–06 contained erroneous 

logic. The NPRM proposed to add 

airplanes to the applicability and to add 

requirements to replace the existing 

SWCs with new, improved SWCs and to 

modify the airplane for the new 

replacement of the SWC. The SNPRM 

proposed to reduce the compliance time 

for replacing the SWCs. We are issuing 

this AD to prevent natural stall events 

during operation in icing conditions, 

which could result in loss of control of 

the airplane. 

The European Aviation Safety Agency 

(EASA), which is the Technical Agent 

for the Member States of the European 

Union, has issued EASA Airworthiness 

Directive 2014–0218, dated September 

29, 2014 (referred to after this as the 

Mandatory Continuing Airworthiness 

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

an unsafe condition on certain Saab AB, 

Saab Aeronautics Model 340A (SAAB/ 

SF340A) and SAAB 340B airplanes. The 

MCAI states: 

A few natural stall events, specifically 

when operating in icing conditions, have 

been experienced on SAAB 340 series 

aeroplanes, without receiving a prior stall 

warning. 

This condition, if not corrected, could 

result in loss of control of the aeroplane. 

To address this potential unsafe condition, 

SAAB developed a modified stall warning 

system, incorporating improved stall warning 

logic, and issued Service Bulletin (SB) 340– 

27–098 and SB 340–27–099, providing 

instructions to replace the Stall Warning 

Computer (SWC) with a new SWC, and 

instructions to activate the new SWC. The 

new system included stall warning curves 

optimized for operation in icing conditions, 

which are activated by selection of Engine 

Anti-Ice. 

Consequently, EASA issued AD 2011–0219 

to require installation of the improved SWC. 

After that [EASA] AD was issued, inservice experience with the improved stall 

warning system revealed cases of premature 

stall warning activation during the take-off 

phase. In numerous recorded cases, the onset 

of stall warning occurred without the 6 

minute delay after weight off wheels. 


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76844 Federal Register / Vol. 81, No. 214 / Friday, November 4, 2016 / Rules and Regulations 

This condition, if not corrected, could lead 

to premature stick shaker activation and 

consequent increase in pilot workload during 

the take-off phase, possibly resulting in 

reduced control of the aeroplane. 

To correct this unsafe condition, EASA 

issued AD 2013–0254 retaining the 

requirements of EASA AD 2011–0219, which 

was superseded, to require deactivation of 

the ice speed curves in the improved SWC 

on SAAB 340 aeroplanes, in accordance with 

SAAB SB 340–27–116. 

Since EASA AD 2013–0254 was issued, 

SAAB developed a technical solution to 

eliminate the premature activation of the stall 

warning ice curves and issued SB 340–27– 

120 (modification of the existing Stall 

Warning System installation), SB 340–27– 

121 (activation of improved SWC for 

aeroplanes with a basic wing tip) and SB 

340–27–122 (activation of improved SWC for 

aeroplanes with an extended wing tip). 

SAAB SB 340–27–120 provides modification 

and installation instructions valid for preand post-SB 340–27–097, 340–27–098, SB 

340–27–099 and SB 340–27–116 aeroplanes. 

For aeroplanes modified in accordance with 

SAAB AB mod. No. 2650 and/or mod. No. 

2859 which are no longer registered in 

Canada, SAAB AB issued SAAB AB SB 340– 

27–109 to provide modification and 

installation instructions to remove the ice 

speed curve function. 

For the reasons described above, this 

[EASA] AD retains the requirements of EASA 

AD 2013–0254, which is superseded, and 

requires modification of the Stall Warning 

and Identification System and replacement of 

the SWC with an improved unit. 

You may examine the MCAI in the 

AD docket on the Internet at http:// 

www.regulations.gov by searching for 

and locating Docket No. FAA–2015– 

6544. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. We 

received no comments on the SNPRM 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 SNPRM for 

correcting the unsafe condition; and 

• Do not add any additional burden 

upon the public than was already 

proposed in the SNPRM. 

Related Service Information Under 1 

CFR Part 51 

Saab AB, Saab Aeronautics has issued 

the following service information: 

• Saab Service Bulletin 340–27–109, 

dated April 14, 2014. 

• Saab Service Bulletin 340–27–116, 

dated October 18, 2013. 

• Saab Service Bulletin 340–27–120, 

dated July 11, 2014. 

• Saab Service Bulletin 340–27–121, 

dated July 11, 2014. 

• Saab Service Bulletin 340–27–122, 

dated July 11, 2014. 

The service information describes 

procedures for deactivating the stall 

warning speed curves in the SWCs for 

certain airplanes; replacing the existing 

SWCs with new, improved SWCs; and 

modifying the airplane for the new 

replacement of the SWC. These 

documents are distinct since they apply 

to different airplane models in different 

configurations. This service information 

is reasonably available because the 

interested parties have access to it 

through their normal course of business 

or by the means identified in the 

ADDRESSES section. 

Costs of Compliance 

We estimate that this AD affects 105 

airplanes of U.S. registry. 

The actions required by AD 2012–24– 

06 and retained in this AD, take about 

78 work-hours per product, at an 

average labor rate of $85 per work-hour. 

Required parts cost about $33,000 per 

product. Based on these figures, the 

estimated cost of the actions that were 

required by AD 2012–24–06 is $39,630 

per product. 

The new requirement of this AD adds 

no additional economic burden. 

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. 

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 

removing Airworthiness Directive (AD) 

2012–24–06, Amendment 39–17276 (77 

FR 73279, December 10, 2012), and 

adding the following new AD: 

2016–22–15 Saab AB, Saab Aeronautics: 

Amendment 39–18704; Docket No. 

FAA–2015–6544; Directorate Identifier 

2014–NM–198–AD. 

(a) Effective Date 

This AD is effective December 9, 2016. 

(b) Affected ADs 

This AD replaces AD 2012–24–06, 

Amendment 39–17276 (77 FR 73279, 

December 10, 2012) (‘‘AD 2012–24–06’’). 

(c) Applicability 

This AD applies to Saab AB, Saab 

Aeronautics (formerly known as Saab AB, 

Saab Aerosystems) Model 340A (SAAB/ 

SF340A) and SAAB 340B airplanes, 

certificated in any category, as identified in 

paragraphs (c)(1) and (c)(2) of this AD. 

(1) Model 340A (SAAB/SF340A) airplanes, 

serial numbers 004 through 159 inclusive. 

(2) Model SAAB 340B airplanes, serial 

numbers 160 through 459 inclusive, except 

serial numbers 170, 342, 362, 363, 367, 372, 

379, 385, 395, 405, 409, 431, 441, and 455. 


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(d) Subject 

Air Transport Association (ATA) of 

America Code 27, Flight Controls. 

(e) Reason 

This AD was prompted by a determination 

that airplanes with certain modifications 

were excluded from the applicability in AD 

2012–24–06, and are affected by the 

identified unsafe condition; and the stall 

warning computer (SWC) required by AD 

2012–24–06 contained erroneous logic. We 

are issuing this AD to prevent natural stall 

events during operation in icing conditions, 

which could result in loss of control of the 

airplane. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Deactivation of Stall Speed Curves 

For airplanes identified in paragraphs 

(g)(1) and (g)(2) of this AD: Within 30 days 

after the effective date of this AD, do the 

deactivation specified in paragraph (g)(1) or 

(g)(2) of this AD, as applicable to airplane 

configuration, in accordance with the 

Accomplishment Instructions of Saab Service 

Bulletin 340–27–116, dated October 18, 2013. 

(1) For airplanes with a basic wing tip that 

has been modified using Saab Service 

Bulletin 340–27–098: Deactivate the stall 

speed curves in the SWC having part number 

(P/N) 0020AK6. 

(2) For airplanes with an extended wing tip 

that has been modified using Saab Service 

Bulletin 340–27–099: Deactivate the stall 

speed curves in the SWC having P/N 

0020AK7. 

(h) Replacement of SWCs 

Within 3 months after the effective date of 

this AD: Do the replacement specified in 

paragraph (h)(1) or (h)(2) of this AD, as 

applicable. 

(1) For airplanes with basic wing tips: 

Replace all SWCs with new, improved SWCs 

having P/N 0020AK6–1, in accordance with 

the Accomplishment Instructions of Saab 

Service Bulletin 340–27–121, dated July 11, 

2014. 

(2) For airplanes with extended wing tips: 

Replace all SWCs with new, improved SWCs 

having P/N 0020AK7–1, in accordance with 

the Accomplishment Instructions of Saab 

Service Bulletin 340–27–122, dated July 11, 

2014. 

(i) Concurrent Modification 

Before or concurrently with the 

accomplishment of the applicable 

requirements of paragraph (h) of this AD, do 

the actions specified in paragraph (i)(1) or 

(i)(2) of this AD, as applicable to airplane 

configuration. 

(1) For airplanes on which either Saab AB 

Modification 2650 or Modification 2859 is 

not installed: Modify the stall warning and 

identification system, in accordance with the 

Accomplishment Instructions of Saab Service 

Bulletin 340–27–120, dated July 11, 2014. 

(2) For airplanes on which either Saab AB 

Modification 2650 or Modification 2859 is 

installed, or on which both modifications are 

installed: Modify the stall warning and 

identification system, in accordance with the 

Accomplishment Instructions of Saab Service 

Bulletin 340–27–109, dated April 14, 2014. 

(j) Parts Installation Prohibitions 

After the replacement required by 

paragraph (h) of this AD, no person may 

install any SWC having P/N 0020AK, 

0020AK1, 0020AK2, 0020AK4, 0020AK6, 

0020AK7, or 0020AK3 MOD 1, on any 

airplane. 

(k) 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) 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 

by the Manager, International Branch, ANM– 

116, Transport Airplane Directorate, FAA; or 

the European Aviation Safety Agency 

(EASA); or Saab AB, Saab Aeronautics’ EASA 

Design Organization Approval (DOA). If 

approved by the DOA, the approval must 

include the DOA-authorized signature. 

(l) Related Information 

Refer to Mandatory Continuing 

Airworthiness Information (MCAI) EASA 

Airworthiness Directive 2014–0218, dated 

September 29, 2014, for related information. 

This MCAI may be found in the AD docket 

on the Internet at http://www.regulations.gov 

by searching for and locating Docket No. 

FAA–2015–6544. 

(m) 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 340–27–109, 

dated April 14, 2014. 

(ii) Saab Service Bulletin 340–27–116, 

dated October 18, 2013. 

(iii) Saab Service Bulletin 340–27–120, 

dated July 11, 2014. 

(iv) Saab Service Bulletin 340–27–121, 

dated July 11, 2014. 

(v) Saab Service Bulletin 340–27–122, 

dated July 11, 2014. 

(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 

saab340.techsupport@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 October 

25, 2016. 

Dionne Palermo, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2016–26327 Filed 11–3–16; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2016–9356; Directorate 

Identifier 2016–CE–033–AD; Amendment 

39–18701; AD 2016–22–12] 

RIN 2120–AA64 

Airworthiness Directives; Pilatus 

Aircraft Ltd. Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule; request for 

comments. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for all 

Pilatus Aircraft Ltd. Models PC–6, PC– 

6–H1, PC–6–H2, PC–6/350, PC–6/350– 

H1, PC–6/350–H2, PC–6/A, PC–6/A–H1, 

PC–6/A–H2, PC–6/B–H2, PC–6/B1–H2, 

PC–6/B2–H2, PC–6/B2–H4, PC–6/C–H2, 

and PC–6/C1–H2 airplanes. This AD 

results from mandatory continuing 

airworthiness information (MCAI) 

issued by the aviation authority of 

another country to identify and correct 

an unsafe condition on an aviation 

product. The MCAI describes the unsafe 

condition as wear and cracks on the 

stabilizer-trim attachment and structural 

components. We are issuing this AD to 

require actions to address the unsafe 

condition on these products. 


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