67340 Federal Register / Vol. 79, No. 219 / Thursday, November 13, 2014 / Rules and Regulations 

arising from tiered participation 

arrangements. 

Principle 20: FMI Links 

An FMI that establishes a link with 

one or more FMIs should identify, 

monitor, and manage link-related risks. 

Principle 21: Efficiency and 

Effectiveness 

An FMI should be efficient and 

effective in meeting the requirements of 

its participants and the markets it 

serves. 

Principle 22: Communication 

Procedures and Standards 

An FMI should use, or at a minimum 

accommodate, relevant internationally 

accepted communication procedures 

and standards in order to facilitate 

efficient payment, clearing, settlement, 

and recording. 

Principle 23: Disclosure of Rules, Key 

Procedures, and Market Data 

An FMI should have clear and 

comprehensive rules and procedures 

and should provide sufficient 

information to enable participants to 

have an accurate understanding of the 

risks, fees, and other material costs they 

incur by participating in the FMI. All 

relevant rules and key procedures 

should be publicly disclosed. 

Principle 24: Disclosure of Market Data 

by Trade Repositories 

A trade repository should provide 

timely and accurate data to relevant 

authorities and the public in line with 

their respective needs. 

By order of the Board of Governors of the 

Federal Reserve System, November 6, 2014. 

Robert deV. Frierson, 

Secretary of the Board. 

[FR Doc. 2014–26791 Filed 11–12–14; 8:45 am] 

BILLING CODE P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2014–0437; Directorate 

Identifier 2012–CE–036–AD; Amendment 

39–18019; AD 2014–23–03] 

RIN 2120–AA64 

Airworthiness Directives; Piper 

Aircraft, Inc. 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are superseding 

Airworthiness Directive (AD) 76–06–09 

for certain Piper Aircraft, Inc. Model 

PA–31P airplanes. AD 76–06–09 

required repetitive inspection of certain 

exhaust system parts with replacement 

of parts mating with the turbocharger, as 

necessary, and allowed installation of a 

certain tailpipe v-band coupling as 

terminating action. This new AD 

requires the use of new service 

information and expands the scope of 

the inspections of the turbocharger 

exhaust system. This AD was prompted 

by reports of exhaust system failures, 

new service information, and the 

tailpipe v-band coupling used for 

terminating action is obsolete. We are 

issuing this AD to correct the unsafe 

condition on these products. 

DATES: This AD is effective December 

18, 2014. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in this AD 

as of December 18, 2014. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain other publications listed in 

this AD as of July 17, 2013 (78 FR 

35110, June 12, 2013). 

ADDRESSES: For service information 

identified in this AD, contact Piper 

Aircraft, Inc., 2926 Piper Drive, Vero 

Beach, Florida 32960; telephone: (772) 

567–4361; fax: (772) 978–6573; Internet: 

www.piper.com/home/pages/ 

Publications.cfm; or Lycoming Engines, 

652 Oliver Street, Williamsport, 

Pennsylvania 17701; telephone: (570) 

323–6181; Internet: http:// 

www.lycoming.textron.com/support/ 

publications/index.html; as applicable. 

You may review copies of the 

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. 

Examining the AD Docket 

You may examine the AD docket on 

the Internet at http:// 

www.regulations.govby searching for 

and locating Docket No. FAA–2014– 

0437; 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 (phone: 800–647–5527) is 

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 FURTHER INFORMATION CONTACT: Gary 

Wechsler, Aerospace Engineer, Atlanta 

Aircraft Certification Office, FAA, 1701 

Columbia Avenue, College Park, Georgia 

30337; telephone: (404) 474–5575; fax: 

(404) 474–5606; email: 

gary.wechsler@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to supersede AD 76–06–09, 

Amendment 39–3325 (43 FR 50417, 

October 30, 1978), (‘‘AD 76–06–09’’). 

AD 76–06–09 applied to certain Piper 

Aircraft, Inc. Model PA–31P airplanes. 

The NPRM published in the Federal 

Register on July 9, 2014 (79 FR 38806). 

The NPRM was prompted by reports of 

exhaust system failure. The NPRM 

proposed to retain certain requirements 

of AD 76–06–09. The NPRM also 

proposed to require the use of the new 

service information and expand the 

scope of the inspections of the 

turbocharger exhaust system. We are 

issuing this AD to correct the unsafe 

condition on these products. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. We 

received no comments on the NPRM (79 

FR 38806, July 9, 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 NPRM (79 FR 

38806, July 9, 2014) for correcting the 

unsafe condition; and 

• Do not add any additional burden 

upon the public than was already 

proposed in the NPRM (79 FR 38806, 

July 9, 2014). 

Costs of Compliance 

We estimate that this AD affects 85 

airplanes of U.S. registry. 

We estimate the following costs to 

comply with this AD: 


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ESTIMATED COSTS

Action Labor cost Parts cost Cost per 

product 

Cost on U.S. 

operators 

Visual inspection .............. 3 work-hours × $85 per hour = $255 ....................... Not applicable ................. $255 $21,675 

Review of maintenance 

records.

.5 work-hour × $85 per hour = $42.50 .................... Not applicable ................. 42 .50 3,612 .50 

We have no way of determining how 

much damage may be found on each 

airplane during the inspection. The 

scope of damage on the exhaust system 

could vary from airplane to airplane due 

to the manner and environments the 

airplane may operate. We estimate the 

following costs to do any necessary 

modification, installation, and/or 

replacement that would be required 

based on the results of the inspection. 

We have no way of determining what 

damage may be found or the number of 

airplanes that might need the 

modification, installation, and/or 

replacement: 

ON-CONDITION COSTS

Action Labor cost Parts cost Cost per 

product 

Modification of the exhaust pipe slip joint .................... 5 work-hours × $85 per hour = $425 ........................... $2,841 $3,266 

Installation of the bracket and clamp assembly ........... 5 work-hours × $85 per hour = $425 ........................... 5,000 5,425 

Replacement of v-band coupling .................................. 2 work-hours × $85 per hour = $170 ........................... 780 950 

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 have 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 

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) 

76–06–09, Amendment 39–3325 (43 FR 

50417, October 30, 1978), and adding 

the following new AD: 

2014–23–03 Piper Aircraft, Inc.: 

Amendment 39–18019; Docket No. 

FAA–2014–0437; Directorate Identifier 

2012–CE–036–AD. 

(a) Effective Date 

This AD is effective December 18, 2014. 

(b) Affected ADs 

This AD supersedes AD 76–06–09, 

Amendment 39–3325 (43 FR 50417, October 

30, 1978). 

(c) Applicability 

This AD applies to Piper Aircraft, Inc. 

Model PA–31P airplanes, serial numbers 

31P–1 through 31P–80 and 31P–7300110 

through 31P–7730012, that are certificated in 

any category. 

(d) Subject 

Joint Aircraft System Component (JASC)/ 

Air Transport Association (ATA) of America 

Code 78, Engine Exhaust. 

(e) Unsafe Condition 

This AD was prompted by reports of 

exhaust system failures, new service 

information issued by the manufacturer, and 

the tailpipe v-band coupling used for 

terminating action is obsolete. We are issuing 

this AD to prevent the possibility of an inflight powerplant fire due to an exhaust 

system failure. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Inspection of Exhaust System 

(1) Within the next 60 hours time-inservice (TIS) after December 18, 2014(the 

effective date of this AD) or within the next 

6 months after December 18, 2014 (the 

effective date of this AD), whichever occurs 

first, and repetitively thereafter at intervals 

not to exceed 60 hours TIS or 6 months, 

whichever occurs first, inspect the parts as 

specified in table 1 of paragraph (g)(1) of this 

AD, if installed. 


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TABLE 1 OF PARAGRAPH (g)(1) OF THIS AD: INSPECTION FOR PIPER AND LYCOMING EXHAUST SYSTEM PARTS

Product/part nomenclature Make Model/part No. 

With a light and mirror or other method 

capable of achieving an equivalent visual 

resolution, inspect for the 

following conditions 

Airplane ................................... Piper ........................................ PA–31P ...................................

Engine ..................................... Lycoming ................................. TIGO–541–E series ................

Pipe, exhaust, right-rear .......... Lycoming ................................. 78012 ...................................... Bulges, cracks, and exhaust leak stains. 

Pipe, exhaust, left-rear ............ Lycoming ................................. 78008 ...................................... Bulges, cracks, and exhaust leak stains. 

Pipe, rear exhaust adapter ..... Lycoming ................................. LW–13027 ............................... Bulges, cracks, and exhaust leak stains. 

Tail pipe assembly, upper ....... Piper ........................................ 46323–05 ................................ Bulges, cracks, and exhaust leak stains. 

Tail pipe assembly, lower ....... Piper ........................................ 48788–05 ................................ Bulges, cracks, and exhaust leak stains. 

V-band coupling ...................... Lycoming ................................. LW–12093–5 ........................... Cracks and exhaust leak stains. 

V-band coupling ...................... Piper ........................................ 555–366 or 557–369 .............. Cracks and exhaust leak stains. 

Isolator (CA–3383–1) .............. Piper ........................................ 467–442 .................................. Cracks, looseness, and distortion. 

Bracket—isolator, upper .......... Piper ........................................ 47014–02 ................................ Cracks, looseness, and distortion. 

Bracket—isolator, lower .......... Piper ........................................ 47013–02 ................................ Cracks, looseness, and distortion. 

(2) If any damage is found in any 

inspection required in paragraph (g)(1) of this 

AD, before further flight, do the corrective 

actions, as applicable, in paragraphs (g)(2)(i) 

through (g)(2)(iv). 

(i) Replace Piper v-band couplings 

exhibiting cracks and/or exhaust leak stains 

with airworthy parts following Piper Aircraft, 

Inc. Mandatory Service Bulletin No. 644E, 

dated May 9, 2012. Replace Lycoming v-band 

couplings exhibiting cracks and/or exhaust 

leak stains with airworthy parts following 

Lycoming Service Instruction No. 1238B, 

Revision B, dated January 6, 2010. 

Note to paragraphs (g)(2)(i) and (h)(2)(iii): 

During replacement of v-band couplings, we 

recommend not opening the v-band coupling 

more than the MINIMUM diameter necessary 

to clear coupled flanges. It is recommended 

to replace any locknuts and/or mating 

couplings with airworthy parts when 

locknuts do not exhibit a prevailing torque 

when installed. 

(ii) Replace Lycoming exhaust system parts 

exhibiting bulges, cracks, and/or exhaust leak 

stains with airworthy parts following 

Lycoming Service Instruction No. 1320, 

dated March 7, 1975; or Textron Lycoming 

Service Instruction No. 1391, dated October 

5, 1979, as applicable. 

(iii) Replace Piper tail pipe assembly parts 

exhibiting bulges, cracks, and/or exhaust leak 

stains with airworthy parts following Piper 

Aircraft, Inc. Mandatory Service Bulletin No. 

644E, dated May 9, 2012. 

(iv) Replace Piper isolators and brackets 

exhibiting cracks, looseness and/or distortion 

following Piper Aircraft Corporation Service 

Bulletin No. 462A, dated November 3, 1975; 

and Piper Aircraft, Inc. Mandatory Service 

Bulletin No. 492A, dated May 29, 2012. 

(h) Exhaust System Modifications 

(1) Within the next 100 hours TIS after 

December 18, 2014 (the effective date of this 

AD) or within the next 12 months after 

December 18, 2014 (the effective date of this 

AD), whichever occurs first, review the 

airplane maintenance records to positively 

identify whether the modifications described 

in paragraphs (h)(1)(i) through (h)(1)(iii) of 

this AD have been done. 

(i) Exhaust pipe slip joint modification 

following Piper Aircraft, Inc. Mandatory 

Service Bulletin No. 492A, dated May 29, 

2012; and Textron Lycoming Mandatory 

Service Bulletin No. 393C, dated November 

26, 1976. 

(ii) Installation of bracket and clamp 

assembly following Piper Kit No. 760–974 as 

specified in Piper Aircraft, Inc. Mandatory 

Service Bulletin No. 492A, dated May 29, 

2012; or Piper Aircraft, Inc. Service Bulletin 

462A, dated November 3, 1975. 

(iii) Replacement of Piper v-band coupling, 

part number 556–053, with Piper v-band 

coupling, part number 557–369, following 

Piper Aircraft, Inc. Mandatory Service 

Bulletin No. 644E, dated May 9, 2012. 

(2) If you cannot positively identify that 

the modifications described in paragraphs 

(h)(1)(i) through (h)(1)(iii) of this AD have 

been done, before further flight, you must do 

the modifications described in paragraphs 

(h)(2)(i) through (h)(2)(iii), as applicable. 

(i) Exhaust pipe slip joint modification 

following Piper Aircraft, Inc. Mandatory 

Service Bulletin No. 492A, dated May 29, 

2012, and Textron Lycoming Mandatory 

Service Bulletin SB 393C, dated November 

26, 1976. 

(ii) Installation of bracket and clamp 

assembly following Piper Kit No. 760–974 as 

specified in Piper Aircraft, Inc. Mandatory 

Service Bulletin No. 492A, dated May 29, 

2012; or Piper Aircraft Corporation Service 

Bulletin 462A, dated November 3, 1975. 

(iii) Replacement of Piper v-band coupling, 

part number 556–053, with Piper v-band 

coupling, part number 557–369, following 

Piper Aircraft, Inc. Mandatory Service 

Bulletin No. 644E, dated May 9, 2012. 

(i) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Atlanta Aircraft 

Certification Office (ACO), 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 manager of the ACO, send it to the 

attention of the person identified in the 

Related Information, paragraph (j)(1) of this 

AD. 

(2) 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. 

(j) Related Information 

For more information about this AD, 

contact Gary Wechsler, Aerospace Engineer, 

Atlanta ACO, FAA, 1701 Columbia Avenue, 

College Park, Georgia 30337; telephone: (404) 

474–5575; fax: (404) 474–5606; email: 

gary.wechsler@faa.gov. 

(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 the AD specifies otherwise. 

(3) The following service information was 

approved for IBR on December 18, 2014. 

(i) Piper Aircraft Corporation Service 

Bulletin No. 462A, dated November 3, 1975. 

(ii) Piper Aircraft, Inc. Mandatory Service 

Bulletin No. 492A, dated May 29, 2012. 

(iii) Textron Lycoming Mandatory Service 

Bulletin SB 393C, dated November 26, 1976. 

(4) The following service information was 

approved for IBR on July 17, 2013 (78 FR 

35110, June 12, 2013). 

(i) Piper Aircraft, Inc. Mandatory Service 

Bulletin No. 644E, dated May 9, 2012. 

(ii) Lycoming Service Instruction No. 

1238B, Revision B, dated January 6, 2010. 

(iii) Lycoming Service Instruction No. 

1320, dated March 7, 1975. 

(iv) Textron Lycoming Service Instruction 

No. 1391, dated October 5, 1979. 

(5) For the service information identified in 

this AD, contact Piper Aircraft, Inc., 2926 

Piper Drive, Vero Beach, Florida 32960; 

telephone: (772) 567–4361; fax: (772) 978– 

6573; Internet: www.piper.com/home/pages/

Publications.cfm; or Lycoming Engines, 652 

Oliver Street, Williamsport, Pennsylvania 

17701; telephone: (570) 323–6181; Internet: 

http://www.lycoming.textron.com/support/

publications/index.html; as applicable. 

(6) You may review copies of the 

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. 


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(7) 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 Kansas City, Missouri, on 

November 4, 2014. 

Earl Lawrence, 

Manager, Small Airplane Directorate, Aircraft 

Certification Service. 

[FR Doc. 2014–26706 Filed 11–12–14; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2014–0594; Directorate 

Identifier 2014–CE–022–AD; Amendment 

39–18005; AD 2014–22–01] 

RIN 2120–AA64 

Airworthiness Directives; PILATUS 

AIRCRAFT LTD. Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: We are superseding 

Airworthiness Directive (AD) 2012–26– 

16 for all PILATUS AIRCRAFT LTD. 

Models PC–12, PC–12/45, PC–12/47, 

and PC–12/47E 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 need to incorporate new 

revisions into the Limitations section, 

Chapter 4, of the FAA-approved 

maintenance program (e.g., maintenance 

manual). We are issuing this AD to 

require actions to address the unsafe 

condition on these products. 

DATES: This AD is effective December 

18, 2014. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in the AD 

as of December 18, 2014. 

ADDRESSES: You may examine the AD 

docket on the Internet at http://

www.regulations.gov by searching for 

and locating Docket No. FAA–2014– 

0594; 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 20590. 

For service information identified in 

this AD, contact PILATUS AIRCRAFT 

LTD., Customer Service Manager, CH– 

6371 STANS, Switzerland; telephone: 

+41 (0) 41 619 33 33; fax: +41 (0) 41 619 

73 11; Internet: http://www.pilatusaircraft.com or email: SupportPC12@

pilatus-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: 

Doug Rudolph, Aerospace Engineer, 

FAA, Small Airplane Directorate, 901 

Locust, Room 301, Kansas City, 

Missouri 64106; telephone: (816) 329– 

4059; fax: (816) 329–4090; email: 

doug.rudolph@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to add an AD that would apply 

to all PILATUS AIRCRAFT LTD. Models 

PC–12, PC–12/45, PC–12/47, and PC– 

12/47E airplanes. That NPRM was 

published in the Federal Register on 

August 18, 2014 (79 FR 48701), and 

proposed to supersede AD 2012–26–16, 

Amendment 39–17311 (78 FR 11572, 

February 19, 2013). 

Since we issued AD 2012–26–16, 

Amendment 39–17311 (78 FR 11572, 

February 19, 2013), PILATUS 

AIRCRAFT LTD. has issued revisions to 

the Limitations section of the airplane 

maintenance manual to include 

repetitive inspections of the inboard 

flap drive arms for cracks. 

The European Aviation Safety Agency 

(EASA), which is the Technical Agent 

for the Member States of the European 

Community, has issued AD No. 2014– 

0170, dated July 17, 2014 (referred to 

after this as ‘‘the MCAI’’), to correct an 

unsafe condition for the specified 

products. The MCAI states: 

The maintenance instructions and 

airworthiness limitations applicable to the 

Structure and Components of PC–12 

aeroplanes are specified in the Aircraft 

Maintenance Manual (AMM) under Chapter 

4, Airworthiness Limitation Section (ALS). 

The instructions contained in the ALS 

document have been identified as mandatory 

actions for continued airworthiness and 

failure to comply with these instructions and 

limitations could potentially lead to an 

unsafe condition. 

Pilatus Aircraft Ltd. recently issued Pilatus 

PC–12 AMM report 02049 issue 28 for PC– 

12, PC–12/45 and PC–12/47 aeroplanes and 

PC–12 AMM report 02300 issue 11 for PC– 

12/47E aeroplanes to incorporate new 

repetitive inspection intervals of the inboard 

flap drive arms because of the detection of 

cracked parts. 

For the reason described above, this AD 

retains the requirements of EASA AD 2013– 

0031, which is superseded, and requires 

implementation of the new maintenance 

requirements and/or airworthiness 

limitations. 

The MCAI can be found in the AD 

docket on the Internet at: http://

www.regulations.gov/

#!documentDetail;D=FAA-2014-0594- 

0003. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. The 

following presents the comments 

received on the proposal and the FAA’s 

response to each comment. 

Request To Remove Actions Retained 

From AD 2012–26–16, Amendment 39– 

17311 (78 FR 11572, February 19, 2013) 

(‘‘AD 2012–26–16’’) 

Johan Kruger, Pilatus Aircraft Ltd., 

requested that we remove the actions 

retained from AD 2012–26–16, 

paragraphs (f)(1) and (f)(2) of the 

proposed AD from the final rule AD 

action. These actions were originally in 

AD 2009–14–13, Amendment 39–15963 

(74 FR 34213, July 15, 2009), which was 

superseded by AD 2012–26–16. 

Johan Kruger stated that the need to 

retain the actions previously required in 

AD 2012–26–16, paragraphs (f)(1) and 

(f)(2) of the proposed AD, no longer 

exists for the following reasons: 

• In AD 2012–26–16, the initial 

compliance time for replacing the nose 

landing gear (NLG) torque tubes part 

number (P/N) 532.50.12.047 on Models 

PC–12 and PC–12/45 airplanes is within 

the next 100 hours time-in-service (TIS) 

after August 19, 2009 (the effective date 

retained from AD 2009–14–13) or 1 year 

after August 19, 2009, whichever occurs 

first. Compliance with this requirement 

should have been completed by 

September 20, 2010. AD 2012–26–16 

also prohibits installing any NLG torque 

tube P/N 532.50.12.047 as of March 26, 

2013 (the effective date retained from 

AD 2012–26–16). 

• Even if P/N 532.50.12.047 had not 

been replaced as required in AD 2012– 

26–16, the life limit for P/N 

532.50.12.047 in the airworthiness 

limitations section (ALS) of the airplane 

maintenance manual (AMM) referenced 

in the proposed AD is deemed adequate 

to address the potential unsafe 

condition. 

• Since August 19, 2009, the effective 

date of AD 2009–14–13, Pilatus has not 

provided any P/N 532.50.12.047 as 

spares to any owners/operators in the 

United States. Pilatus is implying that 


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