This section of the FEDERAL REGISTER

contains regulatory documents having general

applicability and legal effect, most of which

are keyed to and codified in the Code of

Federal Regulations, which is published under

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

The Code of Federal Regulations is sold by

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new books are listed in the first FEDERAL

REGISTER issue of each week.

Rules and Regulations Federal Register

37701 

Vol. 78, No. 121 

Monday, June 24, 2013 

SMALL BUSINESS ADMINISTRATION 

13 CFR Part 121 

RIN 3245–AG29 

Small Business Size Standards; 

Educational Services; Correction 

Correction 

In rule document 2013–14263, 

appearing on pages 36083–36084 in the 

issue of Monday, June 17, 2013, make 

the following correction: 

§ 121.201 What size standards has SBA 

identified by North American Industry 

Classification System codes? [Corrected] 

On page 36083, in the table entitled 

‘‘SMALL BUSINESS SIZE STANDARDS 

BY NAICS INDUSTRY’’, in the third 

column, in the third row, ‘‘ 16 35.5’’ 

should read ‘‘$35.5 16’’. 

[FR Doc. C1–2013–14263 Filed 6–21–13; 8:45 am] 

BILLING CODE 1505–01–D 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2013–0223; Directorate 

Identifier 2012–CE–049–AD; Amendment 

39–17468; AD 2013–11–08] 

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 an 

existing 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. 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 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: This AD is effective July 29, 

2013. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in the AD 

as of July 29, 2013. 

ADDRESSES: You may examine the AD 

docket on the Internet at http:// 

www.regulations.gov 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 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. 

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 include an AD that would 

apply to the specified products. That 

NPRM was published in the Federal 

Register on March 7, 2013 (78 FR 

14729), and proposed to supersede AD 

2011–01–14, Amendment 39–16571 76 

FR 5467; February 1, 2011). That NPRM 

proposed to correct an unsafe condition 

for the specified products. The MCAI 

states that: 

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. 

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. 

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. 

Use Latest Revision of the Airplane 

Maintenance Manual 

Pilatus Aircraft stated that the latest 

revision of the Aircraft Maintenance 

Manual (AMM) 01975 be quoted in the 

AD, which is Pilatus PC–6 B2–H2/B2– 

H4 Maintenance Manual, document No. 

01975, Revision No. 17, dated December 

31, 2012. They stated this will prevent 

applications for an alternative method 

of compliance (AMOC) shortly after AD 

release and that the Airworthiness 

Limitations Section (ALS) section 

remained unchanged in this revision of 

the AMM. They stated the AMM update 

was released after the MCAI was 

submitted and the Aircraft Limitations 


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37702 Federal Register / Vol. 78, No. 121 / Monday, June 24, 2013 / Rules and Regulations 

document 02334 at Revision No. 3, 

dated July 31, 2012, is correct. 

We agree and have added the 

reference to Pilatus PC–6 B2–H2/B2–H4 

Maintenance Manual, document No. 

01975, Revision No. 17, dated December 

31, 2012 in paragraph (f)(1) of this AD. 

Requested Change to Compliance Time 

Pilatus Aircraft stated they found the 

specified compliance time complicated 

and not as intended in the ALS, 

therefore, they request the FAA use the 

compliance time and grace period as 

specified in the EASA AD 2012–0268 or 

Pilatus proposes a flight hour limitation 

also be added to paragraph (f)(3)(ii) in 

the NPRM. Pilatus commented that 

should an operator have more than 8 

years but less than 8.5 years actuator 

service with no flight hour limitation, 

the operator with extreme operating 

hours may exceed the allowed 3,500- 

hour TIS or 350-hour TIS grace period. 

We agree with this comment. We have 

revised paragraph (f)(3) to require 

replacement of the actuator if it has 

accumulated 3,500 hours TIS or 7 years 

or more since new or since last 

overhauled, with a 350-hour TIS or 6- 

month grace period. 

Conclusion 

We reviewed the relevant data, 

considered the comments received, and 

determined that air safety and the 

public interest require adopting the AD 

with the changes described previously 

and minor editorial changes. We have 

determined that these minor changes: 

• Are consistent with the intent that 

was proposed in the NPRM (78 FR 

14729, March 7, 2013) for correcting the 

unsafe condition; and 

• Do not add any additional burden 

upon the public than was already 

proposed in the NPRM (78 FR 14729, 

March 7, 2013). 

We also determined that these 

changes will not increase the economic 

burden on any operator or increase the 

scope of the AD. 

Costs of Compliance 

We estimate that this AD will affect 

15 products of U.S. registry. We also 

estimate that it would take about 7 

work-hours per product to comply with 

the basic requirements of this AD. The 

average labor rate is $85 per work-hour. 

Based on these figures, we estimate 

the cost of the AD on U.S. operators to 

be $8,925, or $595 per product. 

Authority for This Rulemaking 

Title 49 of the United States Code 

specifies the FAA’s authority to issue 

rules on aviation safety. Subtitle I, 

section 106, describes the authority of 

the FAA Administrator. ‘‘Subtitle VII: 

Aviation Programs,’’ describes in more 

detail the scope of the Agency’s 

authority. 

We are issuing this rulemaking under 

the authority described in ‘‘Subtitle VII, 

Part A, Subpart III, Section 44701: 

General requirements.’’ Under that 

section, Congress charges the FAA with 

promoting safe flight of civil aircraft in 

air commerce by prescribing regulations 

for practices, methods, and procedures 

the Administrator finds necessary for 

safety in air commerce. This regulation 

is within the scope of that authority 

because it addresses an unsafe condition 

that is likely to exist or develop on 

products identified in this rulemaking 

action. 

Regulatory Findings 

We determined that this AD will not 

have federalism implications under 

Executive Order 13132. This AD will 

not have a substantial direct effect on 

the States, on the relationship between 

the national government and the States, 

or on the distribution of power and 

responsibilities among the various 

levels of government. 

For the reasons discussed above, I 

certify this AD: 

(1) Is not a ‘‘significant regulatory 

action’’ under Executive Order 12866, 

(2) Is not a ‘‘significant rule’’ under 

the DOT Regulatory Policies and 

Procedures (44 FR 11034, February 26, 

1979), 

(3) Will not affect intrastate aviation 

in Alaska, and 

(4) Will not have a significant 

economic impact, positive or negative, 

on a substantial number of small entities 

under the criteria of the Regulatory 

Flexibility Act. 

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 the NPRM, 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. 

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 Amendment 39–16571 (76 FR 

5467, February 1, 2011) and adding the 

following new AD: 

2013–11–08 Pilatus Aircraft Ltd. Airplanes: 

Amendment 39–17468; Docket No. 

FAA–2013–0223; Directorate Identifier 

2012–CE–049–AD. 

(a) Effective Date 

This airworthiness directive (AD) becomes 

effective July 29, 2013. 

(b) Affected ADs 

This AD supersedes AD number 2011–01– 

14, Amendment 39–16571 (76 FR 5467; 

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. The inspection 

requirements have been revised to 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 

Unless already done, do the following 

actions: 

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

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

July 29, 2013 (the effective date of this AD), 

incorporate the maintenance requirements as 

specified in Chapter 04, Airworthiness 

Limitations, dated July 31, 2012, of the 

Pilatus PC–6 Maintenance Manual; into your 


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Federal Register / Vol. 78, No. 121 / Monday, June 24, 2013 / Rules and Regulations 37703 

FAA-accepted maintenance program 

(maintenance manual). 

Note 2 of paragraph (f)(1) of this AD: 

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, that discusses revision 

16 of the Pilatus PC–6 Maintenance Manual. 

Revision 16 and revision 17 of the Pilatus 

PC–6 Maintenance Manual both contain the 

Chapter 04, Airworthiness Limitations, dated 

July 31, 2012. 

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

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

Before further flight after July 29, 2013 (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: If the 

actuator has accumulated 3,500 hours TIS or 

more since new or last overhauled or 7 years 

or more since new or last overhauled, 

whichever occurs first, replacement of the 

flap actuator (except part numbers 

978.73.14.101 and 978.73.14.103) is required 

within 350 hours TIS after July 29, 2013 (the 

effective date of this AD) or 6 months after 

July 29, 2013 (the effective date of this AD), 

whichever occurs first. Actuators with less 

than 3,500 hours TIS or 7 years since new or 

last overhauled are covered by the ALS 

requirement. 

(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. 

(h) Related Information 

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

dated December 19, 2012; and Pilatus PC–6 

B2–H2/B2–H4 Airplane Maintenance Manual 

(AMM); Document No. 01975, revision 17; 

dated December 31, 2012, for related 

information. For the Pilatus Aircraft Ltd. 

related information use the contact 

information found in paragraph (i)(3) of this 

AD. 

(i) 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. 

(i) Chapter 04, Airworthiness Limitations, 

dated July 31, 2012, of the Pilatus PC–6 

Maintenance Manual. 

(ii) Pilatus PC–6 Airworthiness 

Limitations, Document No. 02334, Revision 

No. 3, dated July 31, 2012. 

(3) For Pilatus Aircraft Ltd. service 

information identified in 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. 

(4) You may view this service information 

at 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. 

(5) You may view this service information 

that is incorporated by reference at the 

National Archives and Records 

Administration (NARA). For information on 

the availability of this material at NARA, call 

202–741–6030, or go to: http:// 

www.archives.gov/federal-register/cfr/ibrlocations.html. 

Issued in Kansas City, Missouri, on May 

22, 2013. 

Earl Lawrence, 

Manager, Small Airplane Directorate, Aircraft 

Certification Service. 

[FR Doc. 2013–14967 Filed 6–21–13; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2012–1327; Directorate 

Identifier 2012–NE–47–AD; Amendment 39– 

17478; AD 2013–12–01] 

RIN 2120–AA64 

Airworthiness Directives; Rolls-Royce 

plc Turbofan Engines 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for all 

Rolls-Royce plc (RR) model RB211 Trent 

768–60, 772–60, and 772B–60 turbofan 

engines. This AD was prompted by lowpressure (LP) compressor blade partial 

airfoil release events. This AD requires 

a one-time ultrasonic inspection of LP 

compressor blades that had 

accumulated more than 2,500 flight 

cycles (FC) since new. We are issuing 

this AD to prevent LP compressor blade 

airfoil separations, engine damage, and 

damage to the airplane. 

DATES: This AD becomes effective July 

29, 2013. The Director of the Federal 

Register approved the incorporation by 

reference of certain publications listed 

in this AD as of July 29, 2013. 

ADDRESSES: The Docket Operations 

office is located at Docket Management 

Facility, U.S. Department of 

Transportation, 1200 New Jersey 

Avenue SE., West Building Ground 

Floor, Room W12–140, Washington, DC 

20590–0001. 

Examining the AD Docket 

You may examine the AD docket on 

the Internet at http:// 

www.regulations.gov; or in person at the 

Docket Operations office 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 street address for 

the Docket Operations office (phone: 

800–647–5527) is provided in the 

ADDRESSES section. Comments will be 

available in the AD docket shortly after 

receipt. 

FOR FURTHER INFORMATION CONTACT: 

Robert Green, Aerospace Engineer, 

Engine Certification Office, FAA, Engine 

& Propeller Directorate, 12 New England 

Executive Park, Burlington, MA 01803; 

phone: 781–238–7754; fax: 781–238– 

7199; email: robert.green@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to include an AD that would 

apply to the specified products. That 

NPRM was published in the Federal 

Register on January 31, 2013 (78 FR 

6749). That NPRM proposed to require 

a one-time ultrasonic C-scan inspection 

of LP compressor blades that have 

accumulated more than 2,500 FC since 

new. The European Aviation Safety 

Agency (EASA) subsequently 

superseded EASA AD 2012–0247, dated 

November 20, 2012, by issuing EASA 

AD 2013–0060, dated March 11, 2013, 

to include a re-inspection requirement 

for certain LP compressor blades that 

were not inspected correctly. 

The new mandatory continuing 

airworthiness information (MCAI) 

states: 

Low-Pressure (LP) compressor partial 

aerofoil blade release events have occurred in 

service on RR Trent 700 engines. While 

primary containment of the released sections 

has been achieved in each case, some of the 


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