Federal Register / Vol. 79, No. 205 / Thursday, October 23, 2014 / Rules and Regulations 63311 

through 3.C.(2) of GE CF6–80E1 SB No. S/B 

73–0121, Revision 1, dated May 29, 2014, to 

do the inspection. 

(C) Compliance time for fuel manifold and 

tube (block) clamp inspection: 

(1) If the engine is a first-run engine, 

inspect the fuel manifold and tube (block) 

clamps within 7,500 FH TSN or within 3 

months after the effective date of this AD, 

whichever occurs later. 

(2) If the engine was previously inspected 

using either of GE CF6–80C2 SB No. S/B 73– 

0414, Revision 1, dated May 29, 2014, or GE 

CF6–80E1 SB No. S/B 73–0121, Revision 1, 

dated May 29, 2014, or earlier versions, then 

inspect the fuel manifold and tube (block) 

clamps within 7,500 FH TSLI or within 3 

months after the effective date of this AD, 

whichever occurs later. 

(3) If the engine is not a first-run engine 

and was not previously inspected using GE 

CF6–80C2 SB No. S/B 73–0414, Revision 1, 

dated May 29, 2014, or GE CF6–80E1 SB No. 

S/B 73–0121, Revision 1, dated May 29, 

2014, or earlier versions, then inspect the 

fuel manifold and tube (block) clamps within 

7,500 FH TSN or within 3 months after the 

effective date of this AD, whichever occurs 

later. 

(iii) Thereafter, inspect fuel manifold, P/Ns 

1303M31G12, 1303M32G12, 2420M70G01, 

and 2420M71G01, and tube (block) clamps, 

replace if required by inspection results, and 

replace the loop clamps within every 7,500 

FH TSLI, using paragraphs (e)(2)(i)(A), 

(e)(2)(i)(B), (e)(2)(ii)(A), and (e)(2)(ii)(B) of 

this AD, as applicable. 

(f) Definition 

(1) For the purposes of this AD, an engine 

shop visit is the induction of an engine into 

the shop where the separation of a major 

engine flange occurs, except that induction 

into the shop for any of the reasons in 

paragraphs (f)(i) through (f)(iv) of this AD is 

not an engine shop visit: 

(i) Induction of an engine into a shop 

solely for removal of the compressor top or 

bottom case for airfoil maintenance, or for 

variable stator vane bushing replacement; 

(ii) Induction of an engine into a shop 

solely for replacement of the turbine rear 

frame; 

(iii) Induction of an engine into a shop 

solely for replacement of the accessory 

gearbox or transfer gearbox, or both; or 

(iv) Induction of an engine into a shop 

solely for core vibration trim balance 

procedure that requires separation of a major 

engine flange. 

(2) For the purposes of this AD, a first-run 

engine is an engine that has not had a shop 

visit since entering service. 

(g) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Engine Certification 

Office, FAA, may approve AMOCs for this 

AD. Use the procedures found in 14 CFR 

39.19 to make your request. 

(2) Previously approved AMOCs for AD 

2009–05–02 (74 FR 8161, February 24, 2009) 

remain approved for the corresponding 

requirements of paragraphs (e)(1) and (e)(2) 

of this AD. 

(h) Related Information 

(1) For more information about this AD, 

contact Kasra Sharifi, Aerospace Engineer, 

Engine Certification Office, FAA, Engine & 

Propeller Directorate, 12 New England 

Executive Park, Burlington, MA. 01803; 

phone (781) 238–7773; fax: (781) 238–7199; 

email: kasra.sharifi@faa.gov. 

(2) For additional details of the under cowl 

fire that prompted this AD, refer to National 

Transportation Safety Board (NTSB) safety 

recommendation (SR) A–13–028. The NTSB 

SR is available on the Internet at http://

www.ntsb.gov/doclib/recletters/2013/A-13- 

028.pdf. 

(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) General Electric Company (GE) CF6– 

80C2 Service Bulletin (SB) No. 73–0326 R04, 

Revision 4, dated December 23, 2009. 

(ii) GE CF6–80C2 SB No. S/B 73–0414, 

Revision 1, dated May 29, 2014. 

(iii) GE CF6–80E1 SB No. 73–0061 R04, 

Revision 4, dated December 23, 2009. 

(iv) GE CF6–80E1 SB No. S/B 73–0121, 

Revision 1, dated May 29, 2014. 

(3) For GE service information identified in 

this AD, contact General Electric Company, 

GE Aviation, Room 285, 1 Neumann Way, 

Cincinnati, OH 45215; phone: (513) 552– 

3272; email: geae.aoc@ge.com. 

(4) You may view this service information 

at the FAA, Engine & Propeller Directorate, 

12 New England Executive Park, Burlington, 

MA. For information on the availability of 

this material at the FAA, call (781) 238–7125. 

(5) You may view this service information 

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 Burlington, Massachusetts, on 

October 7, 2014. 

Kim Smith, 

Acting Directorate Manager, Engine & 

Propeller Directorate, Aircraft Certification 

Service. 

[FR Doc. 2014–24697 Filed 10–22–14; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2014–0345; Directorate 

Identifier 2013–NM–230–AD; Amendment 

39–17998; AD 2014–21–06] 

RIN 2120–AA64 

Airworthiness Directives; Beechcraft 

Corporation (Type Certificate 

Previously Held by Hawker Beechcraft 

Corporation; Raytheon Aircraft 

Company; Beech Aircraft Corporation) 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for certain 

Beechcraft Corporation (Type Certificate 

Previously Held by Hawker Beechcraft 

Corporation; Raytheon Aircraft 

Company; Beech Aircraft Corporation) 

Model 400, 400A, 400T, and MU–300 

airplanes. This AD was prompted by a 

report of a failure of the Acme nut 

threads in a pitch trim actuator (PTA). 

This AD requires an inspection to 

determine if PTAs having a certain 

serial number and part number are 

installed, and replacement if they are 

installed. This AD also requires 

repetitive replacements of PTAs with 

new PTAs or certain overhauled PTAs. 

We are issuing this AD to prevent 

failure of the Acme nut threads in the 

PTA, which could lead to loss of control 

of pitch trim and reduced controllability 

of the airplane. 

DATES: This AD is effective November 

28, 2014. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of November 28, 2014. 

ADDRESSES: For service information 

identified in this AD, contact Beechcraft 

Corporation, TMDC, P.O. Box 85, 

Wichita, KS 67201–0085; telephone 

316–676–8238; fax 316–671–2540; email 

tmdc@beechcraft.com; Internet http://

pubs.beechcraft.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– 


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63312 Federal Register / Vol. 79, No. 205 / Thursday, October 23, 2014 / Rules and Regulations 

0345; 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 

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 FURTHER INFORMATION CONTACT: Ann 

Johnson, Aerospace Engineer, Systems 

and Propulsion Branch, ACE–116W, 

FAA, Wichita Aircraft Certification 

Office (ACO), 1801 Airport Road, Room 

100, Mid-Continent Airport, Wichita, 

KS 67209; phone: 316–946–4105; fax: 

316–946–4107; email: Ann.Johnson@

faa.gov. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 by adding an AD that would 

apply to certain Beechcraft Corporation 

(Type Certificate Previously Held by 

Hawker Beechcraft Corporation; 

Raytheon Aircraft Company; Beech 

Aircraft Corporation) Model 400, 400A, 

400T, and MU–300 airplanes. The 

NPRM published in the Federal Register 

on June 30, 2014 (79 FR 36675). The 

NPRM was prompted by a report of a 

failure of the Acme nut threads in a 

PTA. The NPRM proposed to require an 

inspection to determine if PTAs having 

a certain serial number and part number 

are installed, and replacement if they 

are installed. The NPRM also proposed 

to require repetitive replacements of 

PTAs with new PTAs or certain 

overhauled PTAs. We are issuing this 

AD to prevent failure of the Acme nut 

threads in the PTA, which could lead to 

loss of control of pitch trim and reduced 

controllability of the airplane. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. We 

received no comments on the NPRM (79 

FR 36675, June 30, 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 

36675, June 30, 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 36675, 

June 30, 2014). 

Costs of Compliance 

We estimate that this AD affects 735 

airplanes of U.S. registry. 

We estimate the following costs to 

comply with this AD: 

ESTIMATED COSTS

Action Labor cost Parts cost Cost per product Cost on U.S. operators 

Identification of serial/part 

numbers (735 airplanes).

1 work-hour × $85 per 

hour = $85.

$0 ...................................... $85 .................................... $62,475. 

Replacement of PTA (26 

airplanes).

10 work-hours × $85 per 

hour = $850 per replacement.

$17,334 per replacement $18,184 per replacement $472,784 per replacement. 

Repetitive replacement of 

jackscrew and Acme nut 

on PTAs (735 airplanes).

10 work-hours × $85 per 

hour = $850 per replacement.

$17,334 per replacement $18,184 per replacement $13,365,240 per replacement. 

According to the manufacturer, the 

costs of this AD associated with Hawker 

Beechcraft Service Bulletin SB 27–4100, 

dated March 2012, may be covered 

under warranty, thereby reducing the 

cost impact on affected owners/

operators. We do not control warranty 

coverage for affected individuals. As a 

result, we have included all costs in our 

cost estimate. The costs of the repetitive 

replacement are not covered under 

warranty. However, the PTA 

manufacturer states that it is already 

replacing the Acme nut and jackscrew at 

every overhaul, so the owners/operators 

should not see a cost increase due to 

this repetitive replacement requirement. 

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 

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: 


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Federal Register / Vol. 79, No. 205 / Thursday, October 23, 2014 / Rules and Regulations 63313 

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 adding 

the following new airworthiness 

directive (AD): 

2014–21–06 Beechcraft Corporation (Type 

Certificate Previously Held by Hawker 

Beechcraft Corporation; Raytheon 

Aircraft Company; Beech Aircraft 

Corporation): Amendment 39–17998; 

Docket No. FAA–2014–0345; Directorate 

Identifier 2013–NM–230–AD. 

(a) Effective Date 

This AD is effective November 28, 2014. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to the airplanes identified 

in paragraphs (c)(1) and (c)(2) of this AD, 

certificated in any category. 

(1) Beechcraft Corporation (Type 

Certificate Previously Held by Hawker 

Beechcraft Corporation; Raytheon Aircraft 

Company; Beech Aircraft Corporation) 

airplanes identified in paragraphs (c)(1)(i), 

(c)(1)(ii), and (c)(1)(iii) of this AD. 

(i) Model 400 Beechjet airplanes having 

serial numbers RJ–1 through RJ–65, 

inclusive. 

(ii) Model 400A Beechjet airplanes having 

serial numbers RK–1 through RK–604, 

inclusive. 

(iii) Model 400T Beechjet airplanes having 

serial numbers TT–1 through TT–180, 

inclusive; and TX–1 through TX–13, 

inclusive. 

(2) Beechcraft Corporation (Type 

Certificate Previously Held by Hawker 

Beechcraft Corporation; Raytheon Aircraft 

Company; Mitsubishi Heavy Industries, Inc. 

Ltd.) Model MU–300 airplanes, having serial 

numbers A003SA through A093SA, 

inclusive. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 27, Flight Controls. 

(e) Unsafe Condition 

This AD was prompted by a report of a 

failure of the Acme nut threads in a pitch 

trim actuator (PTA). We are issuing this AD 

to prevent failure of the Acme nut threads in 

the PTA, which could lead to loss of control 

of pitch trim and reduced controllability of 

the airplane. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Determination of Serial Number and Part 

Number 

Within 200 flight hours or 6 months after 

the effective date of this AD, whichever 

occurs first, inspect to determine the serial 

number and part number of the PTA, in 

accordance with the Accomplishment 

Instructions of Hawker Beechcraft Service 

Bulletin SB 27–4100, dated March 2012. A 

review of manufacturer delivery and operator 

maintenance records is acceptable in lieu of 

the inspection, if the serial number and part 

number of the PTA can be conclusively 

determined from that review. 

(h) Replacement 

If any serial number and part number 

found during any inspection required by 

paragraph (g) of this AD is one listed in Table 

1 or Table 2 of Hawker Beechcraft Service 

Bulletin SB 27–4100, dated March 2012: 

Within 200 flight hours or 6 months after the 

effective date of this AD, whichever occurs 

first, replace the PTA with a serviceable PTA 

or an overhauled PTA having an Acme nut 

and jackscrew replaced with a new Acme nut 

and jackscrew, in accordance with the 

Accomplishment Instructions of Hawker 

Beechcraft Service Bulletin SB 27–4100, 

dated March 2012. 

(i) Repetitive Replacements 

Within 1,800 flight hours after the effective 

date of this AD, or at the next PTA overhaul, 

whichever occurs first, replace the PTA with 

a new PTA or an overhauled PTA having the 

Acme nut and jackscrew replaced with a new 

Acme nut and jackscrew, in accordance with 

sections 3.A.(2), (3), and (5) through (10) of 

Hawker Beechcraft Service Bulletin SB 27– 

4100, dated March 2012. Repeat the 

replacement thereafter at intervals not to 

exceed 1,800 flight hours, or at every PTA 

overhaul, whichever occurs first. 

(j) 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 

paragraph (k) 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. 

(k) Related Information 

For more information about this AD, 

contact Ann Johnson, Aerospace Engineer, 

Systems and Propulsion Branch, ACE–116W, 

FAA, Wichita Aircraft Certification Office 

(ACO), 1801 Airport Road, Room 100, MidContinent Airport, Wichita, KS 67209; 

phone: 316–946–4105; fax: 316–946–4107; 

email: Ann.Johnson@faa.gov. 

(l) 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) Hawker Beechcraft Service Bulletin SB 

27–4100, dated March 2012. 

(ii) Reserved. 

(3) For service information identified in 

this AD, contact Beechcraft Corporation, 

TMDC, P.O. Box 85, Wichita, KS 67201– 

0085; telephone 316–676–8238; fax 316–671– 

2540; email tmdc@beechcraft.com; Internet 

http://pubs.beechcraft.com. 

(4) You may view this service information 

at 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. 

(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 Renton, Washington, on October 

13, 2014. 

Michael Kaszycki, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2014–24963 Filed 10–22–14; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF HOMELAND 

SECURITY 

U.S. Customs and Border Protection 

19 CFR Part 122 

Notice of Arrival Restrictions 

Applicable to Flights Carrying Persons 

Who Have Recently Traveled to, From, 

or Through Certain Ebola-Stricken 

Countries 

AGENCY: U.S. Customs and Border 

Protection; Department of Homeland 

Security. 

ACTION: Notice of arrival restrictions. 

SUMMARY: This document announces the 

decision of the Commissioner of CBP to 

direct all flights to the U.S. carrying 

persons who have recently traveled to, 

from, or through Ebola-stricken 

countries to arrive at one of the U.S. 

airports where CBP is implementing 

enhanced screening procedures. 

DATES: Effective October 21, 2014. 

FOR FURTHER INFORMATION CONTACT: 

Francis Russo, Office of Field 

Operations, (202) 325–4835, ofo-opscat@cbp.dhs.gov. 

SUPPLEMENTARY INFORMATION: 

Background 

According to the Centers for Disease 

Control and Prevention (CDC), the 


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