Federal Register / Vol. 78, No. 29 / Tuesday, February 12, 2013 / Rules and Regulations 9779 

(e) Compliance 

You are responsible for performing each 

action required by this AD within the 

specified compliance time unless it has 

already been accomplished prior to that time. 

(f) Required Actions 

(1) Within 55 hours time-in-service (TIS), 

and thereafter at intervals not to exceed 55 

hours TIS, using a light, visually inspect the 

TRH for a crack in the entire area shown as 

Area C of the TRH in Figure 1 of Eurocopter 

Alert Service Bulletin (ASB) No. EC155– 

05A021, Revision 1, dated July 20, 2011, or 

ASB No. AS365–05.00.60, Revision 2, dated 

October 9, 2012, as applicable to your 

helicopter model. The inspection area is on 

the tail gearbox (TGB) side of the TRH. The 

TGB is shown as (c) in figures 2 and 3 of the 

ASBs. You must pay particular attention to 

the area around the screws, shown as (e) in 

Figure 3 of the ASBs, and the TRH between 

the lower part of the TGB and its fairing, 

shown as (d) in figures 2 and 3 of the ASBs, 

using details D and E of Figure 3 in the ASBs. 

You must turn the tail rotor by hand to 

inspect the entire Area C. 

(2) If there is a crack on the TRH, remove 

the TRH from service. 

(g) Special flight permits 

No special flight permits will be permitted. 

(h) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Safety Management 

Group, FAA, may approve AMOCs for this 

AD. Send your proposal to: Robert Grant, 

Aviation Safety Engineer, Standards Staff, 

Rotorcraft Directorate, FAA, 2601 Meacham 

Blvd., Fort Worth, Texas 76137; telephone 

817–222–5328; email robert.grant@faa.gov. 

(2) For operations conducted under a 14 

CFR part 119 operating certificate or under 

14 CFR part 91, subpart K, we suggest that 

you notify your principal inspector, or 

lacking a principal inspector, the manager of 

the local flight standards district office or 

certificate holding district office, before 

operating any aircraft complying with this 

AD through an AMOC. 

(i) Additional Information 

The subject of this AD is addressed in 

European Aviation Safety Agency AD No. 

2012–0227, dated October 29, 2012. 

(j) Subject 

Joint Aircraft Service Component (JASC) 

Code: 6420, Tail Rotor Head. 

(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. 

(i) Eurocopter Alert Service Bulletin No. 

EC155–05A021, Revision 1, dated July 20, 

2011. 

(ii) Eurocopter Alert Service Bulletin No. 

AS365–05.00.60, Revision 2, dated October 9, 

2012. 

(3) For Eurocopter service information 

identified in this AD, contact American 

Eurocopter Corporation, 2701 N. Forum 

Drive, Grand Prairie, TX 75052; telephone 

(972) 641–0000 or (800) 232–0323; fax (972) 

641–3775; or at http://www.eurocopter.com/ 

techpub. 

(4) You may view this service information 

at FAA, Office of the Regional Counsel, 

Southwest Region, 2601 Meacham Blvd., 

Room 663, Fort Worth, Texas 76137. For 

information on the availability of this 

material at the FAA, call (817) 222–5110. 

(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 Fort Worth, Texas, on January 28, 

2013. 

Lance T. Gant, 

Acting Directorate Manager, Rotorcraft 

Directorate, Aircraft Certification Service. 

[FR Doc. 2013–02581 Filed 2–11–13; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2012–1111; Directorate 

Identifier 2012–NM–114–AD; Amendment 

39–17342; AD 2013–03–07] 

RIN 2120–AA64 

Airworthiness Directives; Hawker 

Beechcraft Corporation (Type 

Certificate Previously Held by 

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 

Hawker Beechcraft Corporation (Type 

Certificate previously held by Raytheon 

Aircraft Company; Beech Aircraft 

Corporation) Model 400A airplanes. 

This AD was prompted by a report that 

the wiring for the 5-volt direct current 

(DC) system is undersized and does not 

have adequate circuit protection for the 

smaller gauge wire. This AD requires 

installing an in-line fuse in the 5-volt 

DC system for each of the five 

instrument lighting control power 

supplies. We are issuing this AD to 

prevent failure of the wiring, which 

could result in smoke in the cockpit, 

loss of cockpit lighting, and potential 

damage to surrounding wiring for other 

cockpit equipment such as the stick 

shaker function or angle-of-attack 

indicators. 

DATES: This AD is effective March 19, 

2013. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in the AD 

as of March 19, 2013. 

ADDRESSES: For service information 

identified in this AD, contact Hawker 

Beechcraft Corporation, Department 62, 

P.O. Box 85, Wichita, KS 67201–0085; 

telephone 316–676–8238; fax 316–676– 

6706; email 

tmdc@hawkerbeechcraft.com; Internet 

https://www.hawkerbeechcraft.com/ 

service_support/pubs. 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 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: 

Richard Rejniak, Aerospace Engineer, 

Electrical Systems and Avionics Branch, 

ACE–119W, FAA, Wichita Aircraft 

Certification Office, 1801 Airport Road, 

Room 100, Mid-Continent Airport, 

Wichita, Kansas 67209; phone: (316) 

946–4128; fax (316) 946–4107; email: 

richard.rejniak@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 published in the Federal 

Register on November 5, 2012 (77 FR 

66411). That NPRM proposed to require 

installing an in-line fuse in the 5-volt 

DC system for each of the five 

instrument lighting control power 

supplies. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. We 


pmangrum on DSK3VPTVN1PROD with RULES
9780 Federal Register / Vol. 78, No. 29 / Tuesday, February 12, 2013 / Rules and Regulations 

received no comments on the NPRM (77 

FR 66411, November 5, 2012) 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 the AD 

as proposed. 

Costs of Compliance 

We estimate that this AD affects 421 

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 

Installation ................................................ 10 work-hours × $85 per hour = $850 .................. $285 $1,135 $477,835 

According to the manufacturer, some 

of the costs of this AD may be covered 

under warranty, thereby reducing the 

cost impact on affected individuals. We 

do not control warranty coverage for 

affected individuals. As a result, we 

have included all costs in our cost 

estimate. 

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: 

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): 

2013–03–07 Hawker Beechcraft 

Corporation (Type Certificate Previously 

Held by Raytheon Aircraft Company; 

Beech Aircraft Corporation): 

Amendment 39–17342; Docket No. 

FAA–2012–1111; Directorate Identifier 

2012–NM–114–AD. 

(a) Effective Date 

This AD is effective March 19, 2013. 

(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) Hawker Beechcraft Corporation (Type 

Certificate previously held by Raytheon 

Aircraft Company; Beech Aircraft 

Corporation) Model 400A airplanes having 

serial numbers RK–45 and RK–49 through 

RK–353 inclusive. 

(2) Hawker Beechcraft Corporation (Type 

Certificate previously held by Raytheon 

Aircraft Company; Beech Aircraft 

Corporation) Model 400A airplanes 

(marketed as Hawker 400XP airplanes) 

having serial numbers RK–354 through RK– 

594 inclusive. 

(d) Subject 

Joint Aircraft System Component (JASC)/ 

Air Transport Association (ATA) of America 

Code 2497; Electrical Power System Wiring. 

(e) Unsafe Condition 

This AD was prompted by a report that the 

wiring for the 5-volt direct current (DC) 

system is undersized and does not have 

adequate circuit protection for the smaller 

gauge wire. We are issuing this AD to prevent 

failure of the wiring, which could result in 

smoke in the cockpit, loss of cockpit lighting, 

and potential damage to surrounding wiring 

for other cockpit equipment such as the stick 

shaker function or angle-of-attack indicators. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Fuse Replacement 

Within 400 flight hours or 12 months after 

the effective date of this AD, whichever 

occurs first, install an in-line fuse assembly 

in the 5-volt DC output circuit on each of the 

five instrument lighting power supplies, in 

accordance with the Accomplishment 

Instructions of Hawker Beechcraft Mandatory 

Service Bulletin SB 33–4002, dated October 

2010. A note in the Accomplishment 

Instructions of Hawker Beechcraft Mandatory 

Service Bulletin SB 33–4002, dated October 

2010, instructs operators to contact Hawker 

Beechcraft if any difficulty is encountered in 

accomplishing that service bulletin. 

However, any deviation from the instructions 

provided in Hawker Beechcraft Mandatory 

Service Bulletin SB 33–4002, dated October 

2010, must be approved as an alternative 

method of compliance (AMOC) under the 

provisions of paragraph (i) of this AD. 

(h) Special Flight Permit 

Special flight permits may be issued in 

accordance with sections 21.197 and 21.199 

of the Federal Aviation Regulations (14 CFR 

21.197 and 21.199) to operate the airplane to 

a location where the airplane can be 

modified (if the operator elects to do so), 

provided that the flight is conducted under 

visual flight rules (VFR) day conditions. 

(i) 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, 


pmangrum on DSK3VPTVN1PROD with RULES
Federal Register / Vol. 78, No. 29 / Tuesday, February 12, 2013 / Rules and Regulations 9781 

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. 

(j) Related Information 

For more information about this AD, 

contact Richard Rejniak, Aerospace Engineer, 

Electrical Systems and Avionics Branch, 

ACE–119W, FAA, Wichita Aircraft 

Certification Office, 1801 Airport Road, 

Room 100, Mid-Continent Airport, Wichita, 

Kansas 67209; phone: (316) 946–4128; fax: 

(316) 946–4107; email: 

richard.rejniak@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. 

(i) Hawker Beechcraft Mandatory Service 

Bulletin SB 33–4002, dated October 2010. 

(ii) Reserved. 

(3) For service information identified in 

this AD, contact Hawker Beechcraft 

Corporation, Department 62, P.O. Box 85, 

Wichita, KS 67201–0085; telephone 316– 

676–8238; fax 316–676–6706; email 

tmdc@hawkerbeechcraft.com; Internet 

https://www.hawkerbeechcraft.com/ 

service_support/pubs. 

(4) You may view this 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. 

(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 January 

30, 2013. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2013–02716 Filed 2–11–13; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2012–1251; Directorate 

Identifier 2012–CE–044–AD; Amendment 

39–17335; AD 2013–03–01] 

RIN 2120–AA64 

Airworthiness Directives; Pacific 

Aerospace Limited Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: We are superseding an 

existing airworthiness directive (AD) for 

all Pacific Aerospace Limited Models 

FU24–954 and FU24A–954 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 aircraft 

operating outside the aircraft aft center 

of gravity (C of G) limits during 

parachute-drop operations. Exceeding C 

of G limits could result in loss of control 

of the aircraft. We are issuing this AD 

to require actions to address the unsafe 

condition on these products. 

DATES: This AD is effective March 19, 

2013. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in the AD 

as of March 19, 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 Pacific 

Aerospace Limited, Hamilton Airport, 

Private Bag, 3027 Hamilton, New 

Zealand; telephone: +64 7 843 6144; fax: 

+64 7 843 6134; email: 

enquiries@aerospace.co.nz; Internet: 

http://www.aerospace.co.nz/. 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 November 30, 2012 (77 FR 

71357), and proposed to supersede AD 

2010–20–18, Amendment 39–16453 (75 

FR 59606, September 28, 2010). 

Since we issued AD 2010–20–18, 

Amendment 39–16453 (75 FR 59606, 

September 28, 2010), information has 

been received that shows that the 

operating limitations should be different 

between turbine engine and piston 

engine Pacific Aerospace Limited 

Models FU24–954 and FU24A–954 

airplanes. 

The Civil Aviation Authority (CAA), 

which is the aviation authority for New 

Zealand, has issued AD DCA/FU24/182, 

dated October 25, 2012 (referred to after 

this as ‘‘the MCAI’’), to correct an unsafe 

condition for the specified products. 

The new MCAI AD supersedes the 

requirements in AD DCA/FU24/179. 

The new MCAI requires adding a 

requirement to install station marking 

placards inside the rear cabin walls and 

inserting a supplement into the airplane 

flight manual (AFM) specifically 

approved for parachuting operations 

that contains detailed information for 

determining the weight and balance of 

the aircraft for turbine engine airplanes. 

This AD also retains all actions in AD 

2010–20–18, Amendment 39–16453 (75 

FR 59606, September 28, 2010), for all 

airplanes. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. We 

received no comments on the NPRM (77 

FR 71357, November 30, 2012) 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 the 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 (77 FR 

71357, November 30, 2012), for 

correcting the unsafe condition; and 

• Do not add any additional burden 

upon the public than was already 

proposed in the NPRM (77 FR 71357, 

November 30, 2012). 


pmangrum on DSK3VPTVN1PROD with RULES