Federal Register / Vol. 78, No. 45 / Thursday, March 7, 2013 / Proposed Rules 14729 

hours TIS on the P/N 83278 engine oil 

pressure switch, replace it with a new, zero 

time, P/N 83278 engine oil pressure switch. 

Record the engine oil pressure switch part 

number, date, and airplane hours in the 

airplane log book. The recorded engine oil 

pressure switch TIS will be used as the 

benchmark for calculation of the 3,000 hour 

TIS limit on the engine oil pressure switch. 

(h) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Wichita 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 section 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. 

(i) Related Information 

(1) For more information about this AD, 

contact Jeff Janusz, Sr. Propulsion Engineer, 

Wichita ACO, FAA, 1801 Airport Road, 

Wichita, KS 67209 phone: (316) 946–4148; 

fax: (316) 946–4107; email: 

jeff.janusz@faa.gov. 

(2) For service information identified in 

this AD, contact Cessna Aircraft Company, 

Product Support, P.O. Box 7706, Wichita, 

Kansas 67277; telephone: (316) 517–5800; fax 

(316) 942–9006; Internet: www.cessna.com/ 

customer-service/technical-publications. 

html. 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 

February 27, 2013. 

Earl Lawrence, 

Manager, Small Airplane Directorate, Aircraft 

Certification Service. 

[FR Doc. 2013–05287 Filed 3–6–13; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2013–0223; Directorate 

Identifier 2012–CE–049–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 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 that would 

supersede an existing AD. 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 failure to 

inspect and maintain stabilizer-trim 

attachment components and the flap 

actuator could result in loss of control. 

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 April 22, 2013. 

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 

65 01; fax: +41 (0) 41 619 65 76; 

Internet: http://www.pilatusaircraft.com/#32. 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; 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–2013–0223; Directorate Identifier 

2012–CE–049–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 December 28, 2010, we issued AD 

2011–01–14, Amendment 39–16571 (76 

FR 5647; February 1, 2011). That AD 

required actions intended to address an 

unsafe condition on the products listed 

above. 

Since we issued AD 2011–01–14, (76 

FR 5647; February 1, 2011), the 

airworthiness limitations of the airplane 

maintenance manual has been updated 

to include the flap actuator, which was 

not included when the limitations were 

initially created. 

The European Aviation Safety Agency 

(EASA), which is the Technical Agent 

for the Member States of the European 

Community, has issued EASA AD No.: 

2012–0268, dated December 19, 2012 

(referred to after this as ‘‘the MCAI’’), to 

correct an unsafe condition for the 

specified products. The MCAI states: 

The mandatory instructions and 

airworthiness limitations applicable to the 

Structure and Components of the PC–6 are 

specified in the Aircraft Maintenance Manual 

(AMM) under Chapter 4 or in the 

Airworthiness Limitations Document (ALS), 

depending on the aeroplane model. 


emcdonald on DSK67QTVN1PROD with PROPOSALS
14730 Federal Register / Vol. 78, No. 45 / Thursday, March 7, 2013 / Proposed Rules 

These documents include the maintenance 

instructions and/or airworthiness limitations 

developed by Pilatus Aircraft Ltd. and 

approved by EASA. Failure to comply with 

these instructions and limitations could 

potentially lead to an unsafe condition. To 

address this potentially unsafe condition 

EASA issued AD 2010–0176 to require 

implementation of maintenance instructions 

and/or airworthiness limitations in 

accordance with Pilatus PC–6 ALS issue 1, 

dated 14 May 2010 and Pilatus PC–6 AMM 

Chapter 4, issue 12, dated 14 May 2010. 

Since that AD was issued, Pilatus Aircraft 

Ltd published Pilatus PC–6 AMM (Number 

01975) Chapter 4, issue 16 and PC–6 ALS 

(Number 02334) issue 3 to introduce a 

threshold for replacement of previously not 

listed Flap Actuator. 

For the reason described above, this AD 

retains the requirement of AD 2010–0176, 

which is superseded, and requires the 

implementation of more restrictive 

maintenance requirements and/or 

airworthiness limitation as specified in issue 

16 of Chapter 4 of AMM and issue 3 of ALS. 

This AD also requires replacement of any 

Flap Actuator which, on the effective date of 

this AD, has accumulated or exceeded 7 

years since new or since last overhaul. 

You may obtain further information by 

examining the MCAI in the AD docket. 

Relevant Service Information 

Pilatus Aircraft Ltd. issued Chapter 

04–00–00, Pilatus PC–6 B2–H2/B2–H4 

Maintenance Manual, document No. 

01975, Revision No. 16, dated July 31, 

2012; and Pilatus PC–6 Airworthiness 

Limitations, Document No. 02334, 

Revision No. 3, dated July 31, 2012. 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 

information and determined the unsafe 

condition exists and is likely to exist or 

develop on other products of the same 

type design. 

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 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 39–16571 (76 FR 

5647; February 1, 2011), and adding the 

following new AD: 

Pilatus Aircraft Limited: Docket No. FAA– 

2013–0223; Directorate Identifier 2012– 

CE–049–AD. 

(a) Comments Due Date 

We must receive comments by April 22, 

2013. 

(b) Affected ADs 

This AD supersedes AD number 2011–01– 

14, Amendment 39–16571 (76 FR 5647; 

February 1, 2011). 

(c) Applicability 

This AD applies to 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, all manufacturer 

serial numbers (MSN), and MSN 2001 

through 2092, that are certificated in any 

category. 

Note 1 of paragraph (c): For MSN 2001– 

2092, these airplanes are also identified as 

Fairchild Republic Company PC–6 airplanes, 

Fairchild Industries PC–6 airplanes, 

Fairchild Heli Porter PC–6 airplanes, or 

Fairchild-Hiller Corporation PC–6 airplanes. 

(d) Subject 

Air Transport Association of America 

(ATA) Code 5: Time Limits. 

(e) Reason 

This AD was prompted by inspection 

requirements of the stabilizer-trim 

attachment components that now include an 

additional inspection requirement for the 

flap actuator. We are issuing this proposed 

AD to update the maintenance program with 

new requirements and limitations. 

(f) Actions and Compliance 

(1) For all affected Models PC–6/B2–H2 

and PC–6/B2–H4: Before further flight after 

the effective date of this AD, incorporate the 

maintenance requirements as specified in 

Chapter 04–00–00, Pilatus PC–6 B2–H2/B2– 

H4 Airplane Maintenance Manual (AMM); 

and Airworthiness Limitations, Document 

No. 01975, Revision No. 16, dated July 31, 

2012; into your FAA-accepted maintenance 

program (maintenance manual). 

(2) For all affected Models PC–6 other than 

the Models PC–6/B2–H2 and PC–6/B2–H4: 

Before further flight after the effective date of 

this AD, incorporate the maintenance 

requirements as specified in Pilatus PC–6 

Airworthiness Limitations, Document No. 

02334, Revision No. 3, dated July 31, 2012, 

into your FAA-accepted maintenance 

program. 

(3) For all Models PC–6 airplanes: This AD 

provides a grace period for the initial 

replacement of the flap actuator (except part 

numbers 978.73.14.101 and 978.73.14.103) 

and replacement is required as indicated: 

(i) If the actuator has accumulated 3,150 

hours or more time-in-service since new or 

overhaul, but does not have more than 8 

years since new or overhaul: Within 350 

hours TIS after the effective date of this AD 

or 6 months after the effective date of this 

AD, whichever occurs first; 

(ii) If the actuator has accumulated 6.5 

years or more since new or overhaul, but 

does not have more than 8 years since new 

or overhaul: Within 350 hours TIS after the 

effective date of this AD or 6 months after the 


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Federal Register / Vol. 78, No. 45 / Thursday, March 7, 2013 / Proposed Rules 14731 

effective date of this AD, whichever occurs 

first; 

(iii) If the actuator has accumulated more 

than 8 years since new or overhaul, but does 

not have 8.5 years or more since new or 

overhaul: No later than accumulating 8.5 

years hours since new or overhaul; or 

(iv) If the actuator has 8.5 years or more 

since new or overhaul: Before further flight 

after the effective date of this AD. 

(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 

ATTN: 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. 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. 

(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. 

(3) Reporting Requirements: For any 

reporting requirement in this AD, a federal 

agency may not conduct or sponsor, and a 

person is not required to respond to, nor 

shall a person be subject to a penalty for 

failure to comply with a collection of 

information subject to the requirements of 

the Paperwork Reduction Act unless that 

collection of information displays a current 

valid OMB Control Number. The OMB 

Control Number for this information 

collection is 2120–0056. Public reporting for 

this collection of information is estimated to 

be approximately 5 minutes per response, 

including the time for reviewing instructions, 

completing and reviewing the collection of 

information. All responses to this collection 

of information are mandatory. Comments 

concerning the accuracy of this burden and 

suggestions for reducing the burden should 

be directed to the FAA at: 800 Independence 

Ave. SW., Washington, DC 20591, Attn: 

Information Collection Clearance Officer, 

AES–200. 

(h) Related Information 

Refer to MCAI EASA AD No.: 2012–0268, 

dated December 19, 2012; Chapter 04–00–00, 

Pilatus PC–6 B2–H2/B2–H4 Airplane 

Maintenance Manual (AMM); and, Pilatus 

PC–6 Airworthiness Limitations, Document 

No. 02334, Revision No. 3, dated July 31, 

2012; for related information. For service 

information related to this AD, contact 

Pilatus Aircraft Ltd., Customer Service 

Manager, CH–6371 STANS, Switzerland; 

telephone: +41 (0) 41 619 65 01; fax: +41 (0) 

41 619 65 76; Internet: http://www.pilatusaircraft.com/#32. 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 March 

1, 2013. 

John Colomy, 

Acting Manager, Small Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2013–05292 Filed 3–6–13; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2013–0204; Directorate 

Identifier 2012–NM–229–AD] 

RIN 2120–AA64 

Airworthiness Directives; The Boeing 

Company 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 

The Boeing Company Model 747–400 

and 747–400F series airplanes. This 

proposed AD was prompted by reports 

of cracking in the outboard flange of the 

longeron extension fittings, which 

attach to the wing-to-body fairing 

support frame. This proposed AD would 

require repetitive inspections of the 

longeron extension fittings for cracking, 

and corrective actions if necessary. We 

are proposing this AD to detect and 

correct cracks in the longeron extension 

fittings, which can become large and 

adversely affect the structural integrity 

of the airplane. 

DATES: We must receive comments on 

this proposed AD by April 22, 2013. 

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: Deliver to Mail 

address above between 9 a.m. and 5 

p.m., Monday through Friday, except 

Federal holidays. 

For Boeing service information 

identified in this proposed AD, contact 

Boeing Commercial Airplanes, 

Attention: Data & Services Management, 

P.O. Box 3707, MC 2H–65, Seattle, WA 

98124–2207; telephone 206–544–5000, 

extension 1; fax 206–766–5680; Internet 

https://www.myboeingfleet.com. You 

may review copies of the referenced 

service information at the FAA, 

Transport Airplane Directorate, 1601 

Lind Avenue SW., Renton, Washington. 

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; 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 

(phone: 800–647–5527) is in the 

ADDRESSES section. Comments will be 

available in the AD docket shortly after 

receipt. 

FOR FURTHER INFORMATION CONTACT: 

Nathan Weigand, Aerospace Engineer, 

Airframe Branch, ANM–120S, FAA, 

Seattle Aircraft Certification Office, 

1601 Lind Avenue SW., Renton, 

Washington 98057–3356; phone: 425– 

917–6428; fax: 425–917–6590; email: 

Nathan.P.Weigand@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Comments Invited 

We invite you to send any written 

relevant data, views, or arguments about 

this proposal. Send your comments to 

an address listed under the ADDRESSES

section. Include ‘‘Docket No. FAA– 

2013–0204; Directorate Identifier 2012– 

NM–229–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:// 

www.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 

We received reports that cracks were 

found in the outboard flanges of the 


emcdonald on DSK67QTVN1PROD with PROPOSALS