64696 Federal Register / Vol. 77, No. 205 / Tuesday, October 23, 2012 / Rules and Regulations 

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): 

2012–21–06 Hawker Beechcraft 

Corporation: Amendment 39–17222; 

Docket No. FAA–2012–0830; Directorate 

Identifier 2012–CE–026–AD. 

(a) Effective Date 

This AD is effective November 27, 2012. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to Hawker Beechcraft 

Corporation Model C90GTi (King Air) 

airplanes, serial numbers LJ–1847, and LJ– 

1853 through LJ–1997, that are certificated in 

any category. 

(d) Subject 

Joint Aircraft System Component (JASC)/ 

Air Transport Association (ATA) of America 

Code 24; Electric power. 

(e) Unsafe Condition 

This AD was prompted by reports of 

incorrect gauge wires used in the wiring 

bundles for the cockpit electrical power for 

backlighting and instrument panel 

components. We are issuing this AD to 

prevent failure of the wiring for the power to 

the airplane’s cockpit backlighting and 

instrument panel components. Failure of the 

wiring for the airplane’s cockpit backlighting 

and instrument panel components could 

cause smoke in the cockpit; loss of power to 

the multifunction display, the co-pilot’s 

primary flight display, and cockpit lighting; 

and potential damage to surrounding wires 

and components. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Replace Cockpit Electrical Power Wires 

Within the next 50 hours time-in-service 

after November 27, 2012 (the effective date of 

this AD) or within the next 6 calendar 

months after November 27, 2012 (the 

effective date of this AD), whichever occurs 

first, do the replacements specified below 

following the Accomplishment Instructions 

in Hawker Beechcraft Mandatory Service 

Bulletin No. SB 24–4050, dated November 

2010: 

(1) Replace wire part number (P/N) CB41– 

J11–1 on the A124 fuel control panel 

assembly with a new wire P/N M22759/16– 

14–9. 

(2) Replace wire P/N J26–4–CB308 on the 

co-pilot primary flight display (PFD) and 

wire P/N J27–5–CB272 on the multifunction 

display (MFD) with a new wire P/N M22759/ 

16–16–9. 

(h) Inspect Associated Wire Bundles and 

Components 

While doing the replacements required in 

paragraphs (g)(1) and (g)(2) of this AD at the 

compliance time specified in paragraph (g) of 

this AD, visually inspect the associated wire 

bundles and components for heat damage. Do 

the inspections following the 

Accomplishment Instructions in Hawker 

Beechcraft Mandatory Service Bulletin No. 

SB 24–4050, dated November 2010. 

(i) Repair or Replace Damaged Wires and/or 

Components 

Before further flight after the inspection 

required in paragraph (h) of this AD, repair 

or replace any heat damaged wires or 

components following the Accomplishment 

Instructions in Hawker Beechcraft Mandatory 

Service Bulletin No. SB 24–4050, dated 

November 2010. 

(j) Special Flight Permit 

Special flight permits are permitted with 

the following limitation: Visual flight rules 

(VFR) day conditions only. 

(k) 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. 

(l) Related Information 

For more information about this AD, 

contact Richard Rejniak, Aerospace Engineer, 

Wichita ACO, FAA, 1801 Airport Road, 

Room 100, Wichita, Kansas 67209; phone: 

(316) 946–4128; fax: (316) 946–4107; email: 

richard.rejniak@faa.gov. 

(m) 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 No. SB 24–4050, dated November 

2010. 

(ii) Reserved. 

(3) For Hawker Beechcraft Corporation 

service information identified in this AD, 

contact Hawker Beechcraft Corporation, 

10511 E. Central Ave., Wichita, Kansas 

67206; phone: (316) 676–3100 or (888) 727– 

4344; fax: (316) 676–3222 or (316) 676–3327; 

email: HBC_Parts@hawkerbeechcraft.com; 

Internet: www.hawkerbeechcraft.com. 

(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 

October 11, 2012. 

John Colomy, 

Acting Manager, Small Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2012–25670 Filed 10–22–12; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2011–0567; Directorate 

Identifier 2010–NM–272–AD; Amendment 

39–17218; AD 2012–21–02] 

RIN 2120–AA64 

Airworthiness Directives; The Boeing 

Company Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for certain 

The Boeing Company Model 767–200, 

–300, –300F, and –400ER series 

airplanes. This AD was prompted by a 

design review following a ground fire 

incident and reports of flammable fluid 

leaks from the wing leading edge area 

onto the engine exhaust area. This AD 

requires modification of the fluid drain 

path in the leading edge area of the 

wing. We are issuing this AD to prevent 

flammable fluid from leaking onto the 

engine exhaust nozzle, which could 

result in a fire. 

DATES: This AD is effective November 

27, 2012. 

The Director of the Federal Register 

approved the incorporation by reference 


tkelley on DSK3SPTVN1PROD with RULES
Federal Register / Vol. 77, No. 205 / Tuesday, October 23, 2012 / Rules and Regulations 64697 

of certain publications listed in the AD 

as of November 27, 2012. 

ADDRESSES: For service information 

identified in this AD, contact Boeing 

Commercial Airplanes, Attention: Data 

& Services Management, P.O. Box 3707, 

MC 2H–65, Seattle, WA 98124–2207; 

phone: 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, 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; 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: 

Tung Tran, Aerospace Engineer, 

Propulsion Branch, ANM–140S, Seattle 

Aircraft Certification Office (ACO), 

FAA, 1601 Lind Avenue SW., Renton, 

WA 98057–3356; phone: 425–917–6505; 

fax: 425–917–6590; email: 

Tung.Tran@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 June 15, 2011 (76 FR 34918). 

That NPRM proposed to require 

modifying the fluid drain path in the 

leading edge area of the wing. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. The 

following presents the comments 

received on the proposal (76 FR 34918, 

June 15, 2011) and the FAA’s response 

to each comment. 

Support for Proposed Rule (76 FR 

34918, June 15, 2011) 

Continental Airlines (Continental) 

stated it agrees with the intent of the 

proposed rule (76 FR 34918, June 15, 

2011). 

Requests To Incorporate New 

Information Notice and Clarify Certain 

Service Information 

Delta Airlines (Delta), American 

Airlines (American), and Continental 

requested that we incorporate Boeing 

Service Bulletin Information Notice 

767–57–0121 IN 01, dated March 3, 

2011, into the NPRM (76 FR 34918, June 

15, 2011). American justified its request 

by stating this information notice 

addresses information critical to the 

correct application of sealant, and, if 

this information notice is not 

incorporated by reference in the AD, the 

modification addressed in Boeing 

Special Attention Service Bulletin 767– 

57–0121, dated October 7, 2010, will be 

incomplete and incorrect. Continental 

justified its request by stating this 

information notice corrects and clarifies 

certain instructions of Boeing Special 

Attention Service Bulletin 767–57– 

0121, dated October 7, 2010. Air New 

Zealand requested clarification of 

exactly where the sealant specified in 

steps 7 and 8 of Figures 11 and 12 is to 

be applied. 

Boeing has requested that we allow 

the use of Boeing Special Attention 

Service Bulletin 767–57–0121, Revision 

1, dated July 27, 2011. Boeing Special 

Attention Service Bulletin 767–57– 

0121, Revision 1, dated July 27, 2011, as 

revised by Boeing Special Attention 

Service Bulletin 767–57–0121, Revision 

2, dated January 10, 2012, includes the 

information contained in Boeing Service 

Bulletin Information Notice 767–57– 

0121 IN 01, dated March 3, 2011. 

We agree to incorporate the content of 

Boeing Service Bulletin Information 

Notice 767–57–0121 IN 01, dated March 

3, 2011, into this final rule. This 

information notice addresses 

information critical to the correct 

application of sealant to the wing ribs. 

We have changed paragraph (g) of this 

AD to refer to Boeing Special Attention 

Service Bulletin 767–57–0121, Revision 

1, dated July 27, 2011, as revised by 

Boeing Special Attention Service 

Bulletin 767–57–0121, Revision 2, dated 

January 10, 2012. We also have added 

paragraph (h) of this AD to give credit 

for modifications of the fluid drain path 

in the leading edge area of the wing, if 

those actions were accomplished before 

the effective date of this AD using 

Boeing Special Attention Service 

Bulletin 767–57–0121, dated October 7, 

2010. We have changed the subsequent 

paragraph designations accordingly. 

Request To Withdraw the NPRM (76 FR 

34918, June 15, 2011) 

UPS requested that we withdraw the 

NPRM (76 FR 34918, June 15, 2011) and 

allow compliance with the actions in 

AD 2011–03–15, Amendment 39–16599 

(76 FR 8615, February 15, 2011) to 

address the identified unsafe condition 

addressed in the NPRM. AD 2011–03– 

15 requires inspecting for correct main 

track downstop assembly, thread 

protrusion, damaged and missing parts 

of the main track downstop assemblies 

of the outboard slats for foreign objects, 

debris, and damage to the wall of the 

track housing of the outboard slats, and 

corrective actions if necessary for 

certain Model 767 series airplanes. UPS 

justified its request by stating that 

Boeing Special Attention Service 

Bulletin 767–57–0118, Revision 1, dated 

October 21, 2010, which is referred to in 

AD 2011–03–15, requires checking all 

the slat track stop bolts and slat track 

housings for debris and correcting any 

discrepancies found, which will correct 

the unsafe condition addressed by the 

NPRM. UPS also stated concern that the 

modification required by the NPRM will 

not address any or all fuel leaking along 

the leading edge of the wing for Model 

767 airplanes, because Boeing Special 

Attention Service Bulletin 767–57– 

0121, dated October 7, 2010, was 

written to change the drain path, but 

was based on a specific incident for 

Model 737 airplane wings. UPS stated 

the modification based on the single 

incident cannot ensure that all 

flammable fuel leaks on Model 767 

airplanes will be addressed by the 

modification specified in the NPRM. 

We disagree with the request to 

withdraw the NPRM (76 FR 34918, June 

15, 2011). AD 2011–03–15, Amendment 

39–16599 (76 FR 8615, February 15, 

2011), was issued to address the 

potential of foreign object damage or slat 

track stop bolts coming loose in the slat 

track housings, which could cause a 

puncture in the track housing when the 

slat is retracted, and a consequent fuel 

leak. The NPRM addressed a wing 

leading edge drain hole that is located 

close to the engine nozzle such that a 

fuel leak from any cause, not just from 

a slat track housing leak, is drained 

directly on the engine exhaust nozzle 

and could cause a fuel fire. 

Accomplishing the actions of AD 2011– 

03–15 does not remove the risk caused 

by the drain hole that is addressed by 

this final rule. We have not changed the 

final rule in this regard. 


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64698 Federal Register / Vol. 77, No. 205 / Tuesday, October 23, 2012 / Rules and Regulations 

Requests To Require New Part Numbers 

for All Modified Parts 

Continental and Delta requested that 

parts modified by accomplishment of 

Boeing Special Attention Service 

Bulletin 767–57–0121, dated October 7, 

2010, be identified with new part 

numbers. Continental justified its 

request by stating that the new part 

numbers are needed to prevent the 

potential of unmodifying a modified 

airplane in the future by purchasing and 

installing an unmodified wing panel on 

that airplane. Delta justified its request 

by stating that the lack of configuration 

control in that service bulletin leaves 

the entire industry at a risk for demodification. Swapping access panels 

between airplanes, which is common 

during C-checks, could create a noncompliance situation if one airplane has 

been modified and the other has not. 

We partially agree. We agree with the 

intent of this request because it prevents 

a situation where unmodified noncompliant parts are installed 

unintentionally due to a lack of 

configuration control. We disagree with 

the commenters’ request for new part 

numbers to be assigned to all modified 

parts, because there are no production 

equivalent parts for these retrofitted 

parts. Therefore, we cannot use the 

production part numbers to identify the 

parts modified per Boeing Special 

Attention Service Bulletin 767–57– 

0121, dated October 7, 2010. However, 

we have changed paragraph (g) of this 

final rule to require actions to be done 

in accordance with Boeing Special 

Attention Service Bulletin 767–57– 

0121, Revision 1, dated July 27, 2011, as 

revised by Boeing Special Attention 

Service Bulletin 767–57–0121, Revision 

2, dated January 10, 2012, which 

includes part marking instructions for 

seal doors, wing panels, and ribs to 

identify that the part was modified per 

this service information. 

Request To Approve Delegation of 

Alternative Methods of Compliance 

(AMOCs) 

Boeing requested paragraph (h) of the 

NPRM (76 FR 34918, June 15, 2011) be 

changed to allow Boeing authority to 

approve AMOCs under the Boeing 

Commercial Airplanes Organization 

Designation Authorization (ODA). 

Boeing justified its request by stating 

that it anticipates repairs will be 

required to panel and ribs etc., when 

Boeing Special Attention Service 

Bulletin 767–57–0121, dated October 7, 

2010, is embodied, and it would be 

beneficial if the Boeing ODA is 

authorized to approve these repairs. 

We agree with the request to delegate 

structural AMOC approval to the Boeing 

ODA, because we believe that the 

Boeing ODA will be effective at making 

those findings. We have added new 

paragraph (i)(3) to the final rule to 

delegate structural AMOC approval to 

the Boeing ODA. 

Change to Proposed Applicability 

We have changed paragraph (c) of this 

final rule to refer to airplanes identified 

in Boeing Special Attention Service 

Bulletin 767–57–0121, Revision 1, dated 

July 27, 2011. 

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 (76 FR 

34918, June 15, 2011) for correcting the 

unsafe condition; and 

• Do not add any additional burden 

upon the public than was already 

proposed in the NPRM (76 FR 34918, 

June 15, 2011). 

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 affects 361 

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 

Leading edge fluid drainage modification ........... 22 work-hours × $85 per hour = $1,870 ............ $651 $2,521 $910,081 

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: 


tkelley on DSK3SPTVN1PROD with RULES
Federal Register / Vol. 77, No. 205 / Tuesday, October 23, 2012 / Rules and Regulations 64699 

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): 

2012–21–02 The Boeing Company: 

Amendment 39–17218; Docket No. 

FAA–2011–0567; Directorate Identifier 

2010–NM–272–AD. 

(a) Effective Date 

This AD is effective November 27, 2012. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to The Boeing Company 

Model 767–200, –300, –300F, and –400ER 

series airplanes, certificated in any category, 

as identified in Boeing Special Attention 

Service Bulletin 767–57–0121, Revision 1, 

dated July 27, 2011. 

(d) Subject 

Joint Aircraft System Component (JASC)/ 

Air Transport Association (ATA) of America 

Code 57, Wings. 

(e) Unsafe Condition 

This AD was prompted by a design review 

following a ground fire incident and reports 

of flammable fluid leaks from the wing 

leading edge area onto the engine exhaust 

area. We are issuing this AD to prevent 

flammable fluid from leaking onto the engine 

exhaust nozzle, which could result in a fire. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Drain Path Modification 

Within 60 months after the effective date 

of this AD, modify the fluid drain path in the 

leading edge area of the wing, in accordance 

with the Accomplishment Instructions of 

Boeing Special Attention Service Bulletin 

767–57–0121, Revision 1, dated July 27, 

2011, as revised by Boeing Special Attention 

Service Bulletin 767–57–0121, Revision 2, 

dated January 10, 2012. 

(h) Credit for Previous Actions 

This paragraph provides credit for the 

modification required by paragraph (g) of this 

AD, if that modification was performed 

before the effective date of this AD using 

Boeing Special Attention Service Bulletin 

767–57–0121, dated October 7, 2010, which 

is not incorporated by reference in this AD. 

(i) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Seattle 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. 

Information may be emailed to: 9-ANMSeattle-ACO-AMOC-Requests@faa.gov. 

(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. 

(3) An AMOC that provides an acceptable 

level of safety may be used for any repair 

required by this AD if it is approved by the 

Boeing Commercial Airplanes Organization 

Designation Authorization (ODA) that has 

been authorized by the Manager, Seattle 

ACO, to make those findings. For a repair 

method to be approved, the repair must meet 

the certification basis of the airplane, and the 

approval must specifically refer to this AD. 

(j) Related Information 

(1) For more information about this AD, 

contact Tung Tran, Aerospace Engineer, 

Propulsion Branch, ANM–140S, Seattle 

Aircraft Certification Office (ACO), FAA, 

1601 Lind Avenue SW., Renton, WA 98057– 

3356; phone: 425–917–6505; fax: 425–917– 

6590; email: Tung.Tran@faa.gov. 

(2) For service information identified in 

this AD, contact Boeing Commercial 

Airplanes, Attention: Data & Services 

Management, P.O. Box 3707, MC 2H–65, 

Seattle, WA 98124–2207; phone: 206–544– 

5000, extension 1; fax: 206–766–5680; 

Internet: https://www.myboeingfleet.com. 

(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) Boeing Special Attention Service 

Bulletin 767–57–0121, Revision 1, dated July 

27, 2011. 

(ii) Boeing Special Attention Service 

Bulletin 767–57–0121, Revision 2, dated 

January 10, 2012. 

(3) For service information identified in 

this AD contact, Boeing Commercial 

Airplanes, Attention: Data & Services 

Management, P.O. Box 3707, MC 2H–65, 

Seattle, WA 98124–2207; phone: 206–544– 

5000, extension 1; fax: 206–766–5680; 

Internet: https://www.myboeingfleet.com. 

(4) You may review copies of the 

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. 

(5) You may also review copies of the 

service information that is incorporated by 

reference at the National Archives and 

Records Administration (NARA). For 

information on the availability of this 

material at an NARA facility, call 202–741– 

6030, or go to http://www.archives.gov/ 

federal-register/cfr/ibr-locations.html. 

Issued in Renton, Washington, on October 

9, 2012. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2012–25672 Filed 10–22–12; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2012–0448; Directorate 

Identifier 2010–SW–016–AD; Amendment 

39–17223; AD 2012–21–07] 

RIN 2120–AA64 

Airworthiness Directives; Agusta 

S.p.A. Helicopters 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for Agusta 

S.p.A. (Agusta) Model A109S 

helicopters to require modifying the 

electrical power distribution system to 

carry a higher electrical load. This AD 

was prompted by an electrical failure on 

an Agusta Model A109E helicopter that 

resulted from ‘‘inadequate functioning 

of the 35 amperes (amps) BATT BUS 

circuit breaker.’’ The actions of this AD 

are intended to require modifying the 

electrical power distribution system to 

prevent failure of the circuit breaker, 

loss of electrical power to instruments 

powered by the ‘‘BATT BUS’’ system, 

and subsequent loss of control of the 

helicopter. 

DATES: This AD is effective November 

27, 2012. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain document listed in this AD 

as of November 27, 2012. 

ADDRESSES: For service information 

identified in this AD, contact Agusta, 

S.p.A., Via Giovanni Agusta 520, 21017 

Cascina Costa di Samarate (VA), Italy, 

ATTN: Giovanni Cecchelli; telephone 

39–0331–711133; fax 39–0331–711180; 

or at http://www.agustawestland.com/ 

technical-bullettins. You may review the 

referenced service information at the 

FAA, Office of the Regional Counsel, 

Southwest Region, 2601 Meacham 

Blvd., Room 663, Fort Worth, Texas 

76137. 

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 


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