Federal Register / Vol. 77, No. 122 / Monday, June 25, 2012 / Rules and Regulations 37781 

under the criteria of the Regulatory 

Flexibility Act. 

We prepared an economic evaluation 

of the estimated costs to comply with 

this AD and placed it in the AD docket. 

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): 

2012–12–10 Agusta S.p.A. Helicopters: 

Amendment 39–17090; Docket No. 

FAA–2012–0013; Directorate Identifier 

2010–SW–043–AD. 

(a) Applicability 

This AD applies to Agusta S.p.A. (Agusta) 

Model AB139 and AW139 helicopters, with 

a generator control unit (GCU), part-number 

(P/N) 1152550–3 installed; certificated in any 

category. 

(b) Unsafe Condition 

This AD defines the unsafe condition as a 

potential fault in the overvoltage protection 

in GCUs currently installed on Model AB139 

and AW139 helicopters. This condition 

could result in failure of the overvoltage 

protection of the GCU, degraded performance 

of the electrical power generation and 

distribution systems, or fire, and subsequent 

loss of control of the helicopter. 

(c) Effective Date 

This AD becomes effective July 30, 2012. 

(d) 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. 

(e) Required Actions 

(1) Remove the No. 1 and No. 2 GCU, P/N 

1152550–3. Do not install GCU, P/N 

1152550–3, on any helicopter. 

(2) Modify the electrical connector A13P1 

(GCU No. 1) and A14P1 (GCU No. 2) by 

installing the wiring to the power 

distribution panel (PDP) for your serialnumbered helicopter as depicted in Figure 1 

of Agusta Bollettino Tecnico No. 139–133, 

Rev. A, dated March 17, 2009. 

(3) Using either GCU P/N 1152550–4 or 

GCU P/N 1152550–5, install a No. 1 and No. 

2 GCU that has the same part number. Having 

different part-numbered GCUs on the same 

helicopter is not approved. 

(f) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Safety Management 

Group, FAA, may approve AMOCs for this 

AD. Send your proposal to: Mark Wiley, 

Aerospace Engineer, FAA, Regulations and 

Policy Group, Rotorcraft Directorate, 2601 

Meacham Blvd., Fort Worth, Texas 76137; 

telephone (817) 222–5134; fax (817) 222– 

5961; email mark.wiley@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. 

(g) Additional Information 

The subject of this AD is addressed in 

European Aviation Safety Agency (EASA) AD 

No. 2009–0042, dated February 25, 2009. 

(h) Subject 

Joint Aircraft Service Component (JASC) 

Code: 2430, DC generating system. 

(i) Material Incorporated by Reference 

(1) The Director of the Federal Register 

approved the incorporation by reference 

(IBR) of the following service information 

under 5 U.S.C. 552(a) and 1 CFR part 51. 

(2) You must use the following service 

information to do the actions required by this 

AD, unless the AD specifies otherwise. 

(3) The following service information was 

approved for IBR on July 10, 2012. 

(i) Agusta Bollettino Tecnico No. 139–133, 

Rev. A, dated March 17, 2009. 

(4) For service information identified in 

this AD, contact Agusta Westland, Customer 

Support & Services, Via Per Tornavento 15, 

21019 Somma Lombardo (VA) Italy, Attn: 

Giovanni Cecchelli; telephone 39–0331– 

711133; fax 39 0331 711180; or at http:// 

www.agustawestland.com/technicalbullettins. 

(5) You may review a copy of the 

referenced service information at the FAA, 

Office of the Regional Counsel, Southwest 

Region, 2601 Meacham Blvd., Room 663, Fort 

Worth, Texas 76137 or 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/code_of_federal_regulations/ 

ibr_locations.html. 

Issued in Fort Worth, Texas, on June 8, 

2012. 

Kim Smith, 

Manager, Rotorcraft Directorate, Aircraft 

Certification Service. 

[FR Doc. 2012–14797 Filed 6–22–12; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2011–1412; Directorate 

Identifier 2011–NM–158–AD; Amendment 

39–17088; AD 2012–12–08] 

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 777–200 

and –300 series airplanes. This AD was 

prompted by reports of cracked retract 

actuator fuse pins that can fail earlier 

than the previously determined safe life 

limit of the pins. A fractured retract 

actuator fuse pin can cause the main 

landing gear to extend without 

restriction and attempt to lock into 

position under high dynamic loads. 

This AD requires an inspection for the 

part number of the fuse pin, and 

replacement of the pin if necessary. We 

are issuing this AD to prevent structural 

damage to the side and drag brace lock 

assemblies, which could result in 

landing gear collapse during 

touchdown, rollout, or taxi. 

DATES: This AD is effective July 30, 

2012. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in the AD 

as of July 30, 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, Washington 98124– 

2207; telephone 206–544–5000, 

extension 1; fax 206–766–5680; Internet 

https://www.myboeingfleet.com. You 

may review copies of the referenced 

service information at the FAA, 

Transport Airplane Directorate, 1601 

Lind Avenue SW., Renton, Washington. 

For information on the availability of 

this material at the FAA, call 425–227– 

1221. 

Examining the AD Docket 

You may examine the AD docket on 

the Internet at http:// 

www.regulations.gov; or in person at the 

Docket Management Facility between 

9 a.m. and 5 p.m., Monday through 

Friday, except Federal holidays. The AD 

docket contains this AD, the regulatory 

evaluation, any comments received, and 


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37782 Federal Register / Vol. 77, No. 122 / Monday, June 25, 2012 / Rules and Regulations 

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: 

James Sutherland, Aerospace Engineer, 

Airframe Branch, ANM–120S, FAA, 

Seattle Aircraft Certification Office, 

1601 Lind Avenue SW., Renton, WA 

98057–3356; phone: 425–917–6533; fax: 

425–917–6590; email: 

james.sutherland@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 December 30, 2011 (76 FR 

82210). That NPRM proposed to require 

an inspection for the part number of the 

fuse pin, and replacement of the pin if 

necessary. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. The 

following presents the comments 

received on the proposal (76 FR 82210, 

December 30, 2011) and the FAA’s 

response to each comment. 

Request To Revise the Compliance 

Time and Include Revised Service 

Information 

Boeing and United Airlines requested 

that we revise the NPRM (76 FR 82210, 

December 30, 2011) to refer to Boeing 

Special Attention Service Bulletin 777– 

32–0083, Revision 2 (not yet released). 

Boeing stated that it had performed a 

new risk-based assessment and found 

that 18 months is adequate to mitigate 

the remaining fleet risk. Boeing 

requested the compliance time be 

changed to 18 months from the date of 

the service bulletin. Also, Boeing 

requested that we provide credit for 

actions accomplished in accordance 

with Boeing Special Attention Service 

Bulletin 777–32–0083, Revision 1, dated 

February 17, 2011. 

We partially agree. We agree to update 

the compliance time to 18 months based 

on the new risk-based safety assessment. 

We revised paragraphs (g), (g)(2), and 

(g)(3) of this AD to reflect an initial 

compliance time of 18 months. We 

disagree with delaying issuance of the 

final rule to reference Boeing Special 

Attention Service Bulletin 777–32– 

0083, Revision 2, because that service 

information is not published at this 

time. Operators may request approval of 

an alternative method of compliance 

(AMOC) once Revision 2 of Boeing 

Special Attention Service Bulletin 777– 

32–0083 is released. 

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 

82210, December 30, 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 82210, 

December 30, 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 proposed AD 

affects 35 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 

Inspection ............................................................ 4 work-hours × $85 per hour = $340 ................. $0 $340 $11,900 

We estimate the following costs to do 

any necessary pin replacements that 

would be required based on the results 

of the inspection. We have no way of 

determining the number of aircraft that 

might need these replacements: 

ON-CONDITION COSTS

Action Labor cost Parts cost Cost per 

product 

Pin replacement ....................................... 1 work-hour × $85 per hour = $85 per 

pin.

$769 per pin ............................................ $854 per pin. 

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 

the DOT Regulatory Policies and 


erowe on DSK2VPTVN1PROD with RULES
Federal Register / Vol. 77, No. 122 / Monday, June 25, 2012 / Rules and Regulations 37783 

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): 

2012–12–08 The Boeing Company: 

Amendment 39–17088; Docket No. 

FAA–2011–1412; Directorate Identifier 

2011–NM–158–AD. 

(a) Effective Date 

This AD is effective July 30, 2012. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to The Boeing Company 

Model 777–200 and –S300 series airplanes; 

certificated in any category; as identified in 

Boeing Special Attention Service Bulletin 

777–32–0083, Revision 1, dated February 17, 

2011. 

(d) Subject 

Joint Aircraft System Component (JASC)/ 

Air Transport Association (ATA) of America 

Code 32: Main landing gear. 

(e) Unsafe Condition 

This AD was prompted by reports of 

cracked retract actuator fuse pins that can fail 

earlier than the previously determined safe 

life limit of the pins. A fractured retract 

actuator fuse pin can cause the main landing 

gear (MLG) to extend without restriction and 

attempt to lock into position under high 

dynamic loads. We are issuing this AD to 

prevent structural damage to the side and 

drag brace lock assemblies, which could 

result in landing gear collapse during 

touchdown, rollout, or taxi. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Inspection of Retract Actuator Fuse Pin 

Within 18 months after the effective date 

of this AD: Inspect the part number of the 

fuse pins of the left and right MLG retract 

actuators, in accordance with the 

Accomplishment Instructions of Boeing 

Special Attention Service Bulletin 777–32– 

0083, Revision 1, dated February 17, 2011. A 

review of airplane maintenance records is 

acceptable in lieu of this inspection if the 

part number of the installed actuator fuse pin 

can be conclusively determined from that 

review. 

(1) If any retract actuator fuse pin having 

part number 112W1769–3 is found installed, 

no further action is required by this 

paragraph for that fuse pin. 

(2) If any retract actuator fuse pin having 

part number 112W1769–1 is found installed 

and the pin has accumulated more than 

10,000 total flight cycles as of the effective 

date of this AD: Within 18 months after the 

effective date of this AD, replace the fuse pin 

with a new part number 112W1769–3 fuse 

pin, in accordance with the Accomplishment 

Instructions of Boeing Special Attention 

Service Bulletin 777–32–0083, Revision 1, 

dated February 17, 2011. 

(3) If any retract actuator fuse pin having 

part number 112W1769–1 is found installed 

and the pin has accumulated 8,000 or more 

total flight cycles, but fewer than or equal to 

10,000 total flight cycles, as of the effective 

date of this AD: Before the accumulation of 

10,000 total flight cycles on the pin, or 

within 18 months after the effective date of 

this AD, whichever occurs later, replace the 

fuse pin with a new part number 112W1769– 

3 fuse pin, in accordance with the 

Accomplishment Instructions of Boeing 

Special Attention Service Bulletin 777–32– 

0083, Revision 1, dated February 17, 2011. 

(4) If any retract actuator fuse pin having 

part number 112W1769–1 is found installed 

and the pin has accumulated fewer than 

8,000 total flight cycles as of the effective 

date of this AD: Before the accumulation of 

8,000 total flight cycles on the pin, or within 

24 months after the effective date of this AD, 

whichever occurs later, replace the fuse pin 

with a new part number 112W1769–3 fuse 

pin, in accordance with the Accomplishment 

Instructions of Boeing Special Attention 

Service Bulletin 777–32–0083, Revision 1, 

dated February 17, 2011. 

(h) Parts Installation 

As of the effective date of this AD, no 

person may install a retract actuator fuse pin 

having part number 112W1769–1 on any 

airplane. 

(i) Credit for Previous Actions 

This paragraph provides credit for actions 

required by paragraph (g) of this AD, if those 

actions were performed before the effective 

date of this AD using Boeing Special 

Attention Service Bulletin 777–32–0083, 

dated February 5, 2009. 

(j) 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 

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. 

(k) Related Information 

For more information about this AD, 

contact James Sutherland, Aerospace 

Engineer, Airframe Branch, ANM–120S, 

FAA, Seattle Aircraft Certification Office, 

1601 Lind Avenue SW., Renton, WA 98057– 

3356; phone: 425–917–6533; fax: 425–917– 

6590; email: james.sutherland@faa.gov. 

(l) Material Incorporated by Reference 

(1) The Director of the Federal Register 

approved the incorporation by reference 

(IBR) of the following service information 

under 5 U.S.C. 552(a) and 1 CFR part 51. 

(2) You must use the following service 

information to do the actions required by this 

AD, unless the AD specifies otherwise. 

(i) Boeing Special Attention Service 

Bulletin 777–32–0083, Revision 1, dated 

February 17, 2011. 

(3) For service information identified in 

this AD, contact Boeing Commercial 

Airplanes, Attention: Data & Services 

Management, P.O. Box 3707, MC 2H–65, 

Seattle, Washington 98124–2207; telephone 

206–544–5000, extension 1; fax 206–766– 

5680; Internet https:// 

www.myboeingfleet.com. 

(4) You may review copies of the 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. 

(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/code_of_federal_regulations/ 

ibr_locations.html. 

Issued in Renton, Washington, on June 7, 

2012. 

Michael Kaszycki, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2012–14544 Filed 6–22–12; 8:45 am] 

BILLING CODE 4910–13–P 


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