Federal Register / Vol. 79, No. 159 / Monday, August 18, 2014 / Proposed Rules 48701 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2014–0594; Directorate 

Identifier 2014–CE–022–AD] 

RIN 2120–AA64 

Airworthiness Directives; Pilatus 

Aircraft LTD. Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to adopt a new 

airworthiness directive (AD) for all 

PILATUS AIRCRAFT LTD. Models PC– 

12, PC–12/45, PC–12/47, and PC–12/

47E airplanes that would supersede AD 

2012–26–16. This proposed AD results 

from mandatory continuing 

airworthiness information (MCAI) 

originated 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 proposed 

AD to require actions to address the 

unsafe condition on these products. 

DATES: We must receive comments on 

this proposed AD by October 2, 2014. 

ADDRESSES: You may send comments by 

any of the following methods: 

• Federal eRulemaking Portal: Go to 

http://www.regulations.gov. Follow the 

instructions for submitting comments. 

• Fax: (202) 493–2251. 

• Mail: U.S. Department of 

Transportation, Docket Operations, M– 

30, West Building Ground Floor, Room 

W12–140, 1200 New Jersey Avenue SE., 

Washington, DC 20590. 

• Hand Delivery: U.S. Department of 

Transportation, Docket Operations, M– 

30, West Building Ground Floor, Room 

W12–140, 1200 New Jersey Avenue SE., 

Washington, DC 20590, between 9 a.m. 

and 5 p.m., Monday through Friday, 

except Federal holidays. 

For service information identified in 

this proposed 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 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– 

0594; 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 proposed AD, the 

regulatory evaluation, any comments 

received, and other information. The 

street address for the Docket Office 

(telephone (800) 647–5527) is in the 

ADDRESSES section. Comments will be 

available in the AD docket shortly after 

receipt. 

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: 

Comments Invited 

We invite you to send any written 

relevant data, views, or arguments about 

this proposed AD. Send your comments 

to an address listed under the 

ADDRESSES section. Include ‘‘Docket No. 

FAA–2014–0594; Directorate Identifier 

2014–CE–022–AD’’ at the beginning of 

your comments. We specifically invite 

comments on the overall regulatory, 

economic, environmental, and energy 

aspects of this proposed AD. We will 

consider all comments received by the 

closing date and may amend this 

proposed AD because of those 

comments. 

We will post all comments we 

receive, without change, to http://

regulations.gov, including any personal 

information you provide. We will also 

post a report summarizing each 

substantive verbal contact we receive 

about this proposed AD. 

Discussion 

On February 8, 2013, we issued AD 

2012–26–16, Amendment 39–17311 (78 

FR 11572, February 19, 2013). That AD 

required actions intended to address an 

unsafe condition on all Pilatus Aircraft 

LTD. Models PC–12, PC–12/45, PC–12/ 

47, and PC–12/47E airplanes and was 

based on mandatory continuing 

airworthiness information (MCAI) 

originated by an aviation authority of 

another country. 

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. 

You may examine the MCAI on the 

Internet at http://www.regulations.gov 

by searching for and locating Docket No. 

FAA–2014–0594. 

Relevant Service Information 

Pilatus Aircraft LTD. has issued 

Structural, Component and 

Miscellaneous—Airworthiness 

Limitations, document 12–A–04–00– 

00–00A–000A–A, dated March 13, 2014, 

and Structural and Component 

Limitations—Airworthiness Limitations, 

document 12–B–04–00–00–00A–000A– 

A, dated March 13, 2014. The actions 

described in this service information are 

intended to correct the unsafe condition 

identified in the MCAI. 

FAA’s Determination and Requirements 

of the Proposed AD 

This product has been approved by 

the aviation authority of another 

country, and is approved for operation 

in the United States. Pursuant to our 

bilateral agreement with this State of 

Design Authority, they have notified us 

of the unsafe condition described in the 

MCAI and service information 

referenced above. We are proposing this 

AD because we evaluated all 


tkelley on DSK3SPTVN1PROD with PROPOSALS
48702 Federal Register / Vol. 79, No. 159 / Monday, August 18, 2014 / Proposed Rules 

information and determined the unsafe 

condition exists and is likely to exist or 

develop on other products of the same 

type design. 

Costs of Compliance 

We estimate that this AD will affect 

770 products of U.S. registry. We also 

estimate that it would take about 16.5 

work-hours per product to comply with 

the basic requirements of this proposed 

AD. The average labor rate is $85 per 

work-hour. Required parts would cost 

about $300 per product. Based on these 

figures, we estimate the cost of this 

proposed AD on U.S. operators to be 

$1,310,925, or $1,702.50 per product. 

This breaks down as follows: 

• New inspections, etc. through 

incorporating maintenance manual 

limitations: 3.5 work-hours with parts 

about $300 for a fleet cost of $460,075, 

or $597.50 per product. 

• Wing main spar fastener holes 

inspection: 12 work-hours with no parts 

cost for fleet cost of $785,400 or $1,020 

per product. 

• Inboard flap drive arm inspection: 1 

work-hour with no parts cost for fleet 

cost of $65,450 or $85 per product. 

In addition, we estimate that any 

necessary corrective actions (oncondition costs) that must be taken 

based on the above inspections, etc. 

would take about 16 work-hours and 

require parts costing approximately 

$10,000 for a cost of $11,360 per 

product. We have no way of 

determining the number of products 

that may need these necessary 

corrective actions. This breaks down as 

follows: 

• Replacements based on damaged 

parts or reduced life limits as a result of 

the new maintenance manual 

limitations: 6 work-hours with parts 

about $4,000 for a cost of $4,510 per 

product. 

• Repairs to the wing spar as a result 

of the wing main spar fastener holes 

inspection: 7 work-hours with parts 

about $5,000 for a cost of $5,595 per 

product. 

• Replacement of the inboard flap 

drive arm as a result of the inboard flap 

drive arm inspection: 3 work-hours with 

parts about $1,000 for a cost of $1,255. 

The only costs that would be imposed 

by this proposed AD over that already 

required by AD 2012–26–16 is the 

inboard flap arm inspection and 

replacement as necessary and the 

addition of 92 airplanes from 678 

airplanes to 770 airplanes. 

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 proposed 

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 proposed AD 

would not have federalism implications 

under Executive Order 13132. This 

proposed AD would 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 this proposed regulation: 

(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. 

The Proposed Amendment 

Accordingly, under the authority 

delegated to me by the Administrator, 

the FAA proposes to amend 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 Amendment 39–17311 (78 FR 

11572, February 19, 2013), and adding 

the following new AD: 

Pilatus Aircraft LTD.: Docket No. FAA– 

2014–0594; Directorate Identifier 2014– 

CE–022–AD. 

(a) Comments Due Date 

We must receive comments by October 2, 

2014. 

(b) Affected ADs 

This AD supersedes AD 2012–26–16, 

Amendment 39–17311 (78 FR 11572, 

February 19, 2013). 

(c) Applicability 

This AD applies to PILATUS AIRCRAFT 

LTD. Models PC–12, PC–12/45, PC–12/47, 

and PC–12/47E airplanes, all manufacturer 

serial numbers (MSNs), certificated in any 

category. 

(d) Subject 

Air Transport Association of America 

(ATA) Code 5: Time Limits. 

(e) Reason 

This AD was prompted by mandatory 

continuing airworthiness information (MCAI) 

originated 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 FAAapproved maintenance program (e.g., 

maintenance manual). The limitations were 

revised to include repetitive inspections of 

the inboard flap drive arms for crack(s). 

These actions are required to ensure the 

continued operational safety of the affected 

airplanes. 

(f) Actions and Compliance 

Unless already done, do the following 

actions in paragraphs (f)(1) through (f)(7) of 

this AD: 

(1) Actions retained from AD 2012–26–16, 

Amendment 39–17311 (78 FR 11572, 

February 19, 2013) for Models PC–12 and 

PC–12/45 airplanes, MSNs 101 through 299: 

Within the next 100 hours time-in-service 

(TIS) after August 19, 2009 (the effective date 

retained from AD 2009–14–13, Amendment 

39–15963 (74 FR 34213, July 15, 2009)) or 1 

year after August 19, 2009 (the effective date 

retained from AD 2009–14–13), whichever 

occurs first, replace the torque tube part 

number (P/N) 532.50.12.047 with torque tube 

P/N 532.50.12.064 following Pilatus Aircraft 

LTD. Service Bulletin No: 32–021, dated 

November 21, 2008. 

(2) Actions retained from AD 2012–26–16, 

Amendment 39–17311 (78 FR 11572, 

February 19. 2013) for all airplanes: As of 

March 26, 2013 (the effective date retained 

from AD 2012–26–16), do not install torque 

tube P/N 532.50.12.047. 

(3) Actions new to this AD for all airplanes: 

Before further flight after September 22, 2014 

(the effective date of this AD), insert Data 

module code 12–A–04–00–00–00A–000A–A, 

‘‘Structural, Component and Miscellaneous— 

Airworthiness Limitations,’’ dated March 13, 

2014, of the Pilatus Model Identification: 12 

Aircraft Maintenance Manual, PC12, PC12/


tkelley on DSK3SPTVN1PROD with PROPOSALS
Federal Register / Vol. 79, No. 159 / Monday, August 18, 2014 / Proposed Rules 48703 

45, PC 12/47 AMM Document No. 02049, 12– 

A–AM–00–00–00–I, revision 28, dated May 

31, 2014, for Models PC–12, PC–12/45, PC– 

12/47, and Data module code 12–B–04–00– 

00–00A–000A–A, ‘‘Structural and 

Component Limitations—Airworthiness 

Limitations,’’ dated March 13, 2014, of the 

Pilatus Model Identification: 12 Aircraft 

Maintenance Manual, PC 12/47E AMM 

Document No. 02300, 12–B–AM–00–00–00– 

I, revision 11, dated May 31, 2014, for Model 

PC–12/47E, into the Limitations section of 

the FAA-approved maintenance program 

(e.g., maintenance manual). These limitations 

section revisions do the following: 

(i) Establish an inspection of the inboard 

flap drive arms, 

(ii) Specify replacement of components 

before or upon reaching the applicable life 

limit, and 

(iii) Specify accomplishment of all 

applicable maintenance tasks within certain 

thresholds and intervals. 

(4) Actions retained from AD 2012–26–16, 

Amendment 39–17311 (78 FR 11572, 

February 19. 2013) for all airplanes: Only 

authorized Pilatus Service Centers can do the 

Supplemental Structural Inspection 

Document (SSID) as required by the 

documents in paragraph (f)(3) of this AD 

because deviations from the type design in 

critical locations could make the airplane 

ineligible for this life extension. 

(5) Actions new to this AD for all airplanes: 

If no compliance time is specified in the 

documents listed in paragraph (f)(3) of this 

AD when doing any corrective actions where 

discrepancies are found as required in 

paragraph (f)(3)(iii) of this AD, do these 

corrective actions before further flight after 

doing the applicable maintenance task. 

(6) Actions new to this AD for all airplanes: 

During the accomplishment of the actions 

required in paragraphs (f)(3)(i), (f)(3)(ii), and 

(f)(3)(iii) of this AD, if a discrepancy is found 

that is not identified in the documents listed 

in paragraph (f)(3) of this AD, before further 

flight after finding the discrepancy, contact 

Pilatus Aircraft LTD, at the address specified 

in paragraph (i) of this AD for a repair 

scheme and incorporate that repair scheme. 

(7) Actions new to this AD for all airplanes: 

Within the next 3 months after the effective 

date of this AD or within the next 150 hours 

TIS after the effective date of this AD, 

whichever occurs first, inspect the inboard 

flap drive arms for cracks and take all 

necessary corrective actions. 

(g) Other FAA AD Provisions 

The following provisions also apply to this 

AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, Standards Office, 

FAA, has the authority to approve AMOCs 

for this AD, if requested using the procedures 

found in 14 CFR 39.19. Send information to 

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. 

(i) Before using any approved AMOC on 

any airplane to which the AMOC applies, 

notify your appropriate principal inspector 

(PI) in the FAA Flight Standards District 

Office (FSDO), or lacking a PI, your local 

FSDO. 

(ii) AMOCs approved for AD 2012–26–16, 

Amendment 39–17311 (77 FR 11572, 

February 19, 2013) are not approved as 

AMOCs for this AD. 

(2) Airworthy Product: For any requirement 

in this AD to obtain corrective actions from 

a manufacturer or other source, use these 

actions if they are FAA-approved. Corrective 

actions are considered FAA-approved if they 

are approved by the State of Design Authority 

(or their delegated agent). You are required 

to assure the product is airworthy before it 

is returned to service. 

(h) Special Flight Permit 

Special flight permits are prohibited. 

(i) Related Information 

Refer to MCAI European Aviation Safety 

Agency (EASA) AD No. 2014–0170, dated 

July 17, 2014, for related information. You 

may examine the MCAI on the Internet at 

http://www.regulations.gov by searching for 

and locating Docket No. FAA–2014–0594. 

For service information related to 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.pilatus-aircraft.com or email: 

SupportPC12@pilatus-aircraft.com. 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. 

Issued in Kansas City, Missouri, on August 

12, 2014. 

Monica L. Nemecek, 

Acting Manager, Small Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2014–19490 Filed 8–15–14; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2014–0570; Directorate 

Identifier 2013–NM–094–AD] 

RIN 2120–AA64 

Airworthiness Directives; Bombardier, 

Inc. Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to adopt a new 

airworthiness directive (AD) for certain 

Bombardier, Inc. Model DHC–8–102, 

–103, –106, –201, –202, –301, –311, and 

–315 airplanes. This proposed AD was 

prompted by fuel system reviews 

conducted by the manufacturer. This 

proposed AD would require revising the 

maintenance or inspection program to 

incorporate new limitations for fuel tank 

systems. We are proposing this AD to 

prevent potential ignition sources 

within the fuel system, which could 

result in a fuel tank explosion. 

DATES: We must receive comments on 

this proposed AD by October 2, 2014. 

ADDRESSES: You may send comments, 

using the procedures found in 14 CFR 

11.43 and 11.45, by any of the following 

methods: 

• Federal eRulemaking Portal: Go to 

http://www.regulations.gov. Follow the 

instructions for submitting comments. 

• Fax: 202–493–2251. 

• Mail: U.S. Department of 

Transportation, Docket Operations, M– 

30, West Building Ground Floor, Room 

W12–140, 1200 New Jersey Avenue SE., 

Washington, DC 20590. 

• Hand Delivery: U.S. Department of 

Transportation, Docket Operations, M– 

30, West Building Ground Floor, Room 

W12–140, 1200 New Jersey Avenue SE., 

Washington, DC, between 9 a.m. and 5 

p.m., Monday through Friday, except 

Federal holidays. 

For service information identified in 

this proposed AD, contact Bombardier, 

Inc., Q-Series Technical Help Desk, 123 

Garratt Boulevard, Toronto, Ontario 

M3K 1Y5, Canada; telephone 416–375– 

4000; fax 416–375–4539; email 

thd.qseries@aero.bombardier.com; 

Internet http://www.bombardier.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. 

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– 

0570; 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 proposed 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. Comments will 

be available in the AD docket shortly 

after receipt. 

FOR FURTHER INFORMATION CONTACT: 

Morton Lee, Propulsion Engineer, 

Propulsion & Services Branch, ANE– 

173; FAA, New York Aircraft 

Certification Office, 1600 Stewart 

Avenue, Suite 410, Westbury, New York 

11590; telephone 516–228–7355; fax 

516–794–5531. 


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