### 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of exhaust system failures, new service information, and the tailpipe v-band coupling used for terminating action is obsolete.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.gov by 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:


### 67341 Federal Register / Vol. 79, No. 219 / Thursday, November 13, 2014 / Rules and Regulations

E STIMATED 

### C OSTS

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:



### O N 

### -C ONDITION 

### C OSTS

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 issuingthis 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.


### 67342 Federal Register / Vol. 79, No. 219 / Thursday, November 13, 2014 / Rules and Regulations

TABLE 

### 1 OF 

### PARAGRAPH 

### (g)(1) OF 

### T HIS 

### AD: I NSPECTION FOR 

### P IPER 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.


### 67343 Federal Register / Vol. 79, No. 219 / Thursday, November 13, 2014 / Rules and Regulations

(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