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

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 powerdistribution 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

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_ 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


## 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:



### E STIMATED 

### C OSTS

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:



### O N 

### -C ONDITION 

### C OSTS

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


## 37783 Federal Register / Vol. 77, No. 122 / Monday, June 25, 2012 / Rules and Regulations

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**