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the airplane (i.e., total of both wing tanks) is limited to 3,500 pounds or less.

(k) Related Information

(1) For further information about this AD, contact Tom Groves, Aerospace Engineer, International Branch, ANM–116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, Washington 98057– 3356; phone: 425–227–1503; fax: 425 227– 1149; email: tom.groves@faa.gov

.

(2) Refer to MCAI Israeli Emergency Airworthiness Directive 28–12–06–18, dated June 24, 2012; and Gulfstream G150 Alert Service Bulletin 150–28A–146, dated June 22, 2012; for related information.
(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) Gulfstream G150 Alert Service Bulletin 150–28A–146, dated June 22, 2012.

(ii) Reserved. (3) For service information identified in this AD, contact Gulfstream Aerospace Corporation, P.O. Box 2206, Mail Station D–25, Savannah, Georgia 31402–2206; telephone 800–810–4853; fax 912–965–3520; email pubs@gulfstream.com ; Internet http:// www.gulfstream.com/product

_ support/ technical

_ pubs/pubs/index.htm

. (4) You may review copies of the 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/code

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Issued in Renton, Washington, on July 13,

2012. Michael Kaszycki, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service.
[FR Doc. 2012–17955 Filed 7–26–12; 8:45 am]

**BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION** 

**Federal Aviation Administration**

**14 CFR Part 39**

**[Docket No. FAA–2012–0356; Directorate Identifier 2011–SW–067–AD; Amendment**  **39–17128; AD 2012–14–14]**

**RIN 2120–AA64**

**Airworthiness Directives; Eurocopter Deutschland GmbH Helicopters** 

**AGENCY :**  Federal Aviation Administration (FAA), DOT.

**ACTION :**  Final rule.

**SUMMARY :**  We are adopting a new airworthiness directive (AD) for all Eurocopter Deutschland GmbH (ECD) MBB–BK 117 A–3, MBB–BK 117 A–4, MBB–BK B–1, MBB–BK 117 B–2, and MBB–BK C–1 helicopters equipped with a certain external-hoist system (hoist system). This AD requires deactivating the entire hoist system or deactivating the hoist system cable cutter function on the hoist system operator control handle (operator handle). This AD was prompted by an uncommanded activation of the hoist cable cutter function on an MBB–BK117 C–1 helicopter. The actions of this AD are intended to prevent uncommanded cutting of the hoist cable and subsequent injury to persons being lifted by the hoist.

**DATES :**  This AD is effective August 31,
2012.

The Director of the Federal Register approved the incorporation by reference of certain documents listed in this AD as of August 31, 2012.

**ADDRESSES :**  For 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.

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 through Friday, except Federal holidays. The AD docket contains this AD, any incorporated-by-reference service information, the economic evaluation, any comments received, and other information. The street address for the Docket Operations Office (phone: 800– 647–5527) is U.S. Department of Transportation, Docket Operations Office, M–30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE., Washington, DC 20590.

**FOR FURTHER INFORMATION CONTACT :**  George Schwab, Aviation Safety Engineer, Safety Management Group, Rotorcraft Directorate, FAA, 2601 Meacham Blvd., Fort Worth, TX 76137; telephone (817) 222–5110; email george.schwab@faa.gov.

**SUPPLEMENTARY INFORMATION :** 

Discussion

On April 4, 2012, at 77 FR 20321, the Federal Register published our notice of proposed rulemaking (NPRM), which proposed to amend 14 CFR part 39 to include an AD that would apply to ECD Model MBB–BK 117 A–3, MBB–BK 117 A–4, MBB–BK B–1, MBB–BK 117 B–2, and MBB–BK C–1 helicopters equipped with a certain hoist system. That NPRM proposed to require deactivating the entire hoist system or deactivating the hoist system cable cutter function on the operator handle. The proposed requirements were intended to prevent uncommanded cutting of the hoist cable and subsequent injury to persons being lifted by the hoist.

The European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Union, has issued EASA AD No. 2011– 0126, dated July 1, 2011 (EASA AD 2011–0126), to correct an unsafe condition for the ECD Model MBB–BK 117 A–3, MBB–BK 117 A–4, MBB–BK B–1, MBB–BK 117 B–2, and MBB–BK C–1 helicopters equipped with a certain hoist system. EASA AD 2011–0126 requires deactivation of the affected external hoist system by pulling and securing the related circuit breakers, or by removing the hoist boom.

After EASA AD 2011–0126 was issued, it was discovered that pulling the circuit breaker WARN ANN II degraded the annunciator system’s redundant power supply, so that pilots could not be warned of a second helicopter system failure. Prompted by these findings, EASA issued superseding EASA AD No. 2011–0131, dated July 8, 2011 (EASA AD 2011– 0131), to require pulling only three circuit breakers (CABLE CUTTER, WINCH CONT, and WINCH BOOM), while circuit breaker WARN ANN II remains inserted.

EASA advises that since EASA AD 2011–0131 was issued ‘‘a corrective action has been developed to establish an adequate safety level, while a terminating action is under


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investigation but currently not available.’’ EASA subsequently issued the current EASA AD No. 2011–0148, dated August 5, 2011 (EASA AD 2011– 0148), which retains the requirements of EASA AD 2011–0131 and requires modification of the helicopter wiring and operator handle, part number (P/N) 76803, a revision to the Rotorcraft Flight Manual and Supplement, and repetitive inspections of the operator handle. EASA AD 2011–0148 also requires implementing a 10-year time frame for overhaul of the operator handle.

Comments

We gave the public the opportunity to participate in developing this AD, but we did not receive any comments on the NPRM.

FAA’s Determination

These helicopters have been approved by the aviation authority of Germany and are approved for operation in the United States. Pursuant to our bilateral agreement with Germany, EASA, its technical representative, has notified us of the unsafe condition described in the EASA AD. We are issuing this AD because we evaluated all information provided by EASA and determined the unsafe condition exists and is likely to exist or develop on other helicopters of these same type designs and that air safety and the public interest require adopting the AD requirements as proposed.

Interim Action

We consider this AD to be an interim action. The design approval holder is currently developing a terminating action to address the unsafe condition identified in this AD. Once this terminating action is developed, approved, and available, we might consider additional rulemaking.

Differences Between This AD and the EASA AD

This AD applies to the ECD Model MBB–BK 117 A–4 model. The EASA AD makes no mention of this model. The EASA AD also applies to the MBB–BK 117 A–1 model. Eurocopter informs us that the MBB–BK 117 A–1 model no longer exists, so we did not include it in our AD. The EASA AD requires temporary revisions to the Rotorcraft Flight Manual and its supplements; this AD does not. The EASA AD requires overhaul of the operator handle every ten years; this AD does not.

Related Service Information

ECD has issued Emergency Alert Service Bulletin MBB–BK117–80–166, Revision 1, dated August 4, 2011 (ASB). The ASB specifies the deactivation of the cable cutter function on the operator handle. After the cable cutter function on the operator handle has been deactivated, the rescue winch may be used. Costs of Compliance

We estimate that this AD will affect about 12 helicopters of U.S. registry.

We estimate the following costs to comply with this AD:

• Option 1: Pull and secure three circuit breakers. We estimate that this task will require about one half-hour to complete. At $85 per work-hour, the labor cost will total about $43. No parts will be needed, so we estimate the total cost per helicopter to be $43, or $516 for the fleet.

• Option 2: Remove the hoist boom from the helicopter. We estimate that this task will require 1.5 hours to complete at $85 per work-hour for a total labor cost of about $128. No parts will be needed, so we estimate the total cost per helicopter to be $128, or $1,536 for the fleet.

• Option 3: We estimate that modifying the hoist operator handle will require four work-hours at $85 per work-hour for a total labor cost of $340 per helicopter. Parts will cost about $92. Inspecting the hoist-operator handle for damage will take about one half-hour for a labor cost of about $43. For 12 monthly inspections per year, the annual cost will total $516. We estimate that replacing the operator handle with a new operator handle will require 0.25 work hour at $85 an hour for a labor cost of about $21 per helicopter. Parts will cost about $18,500 for a total cost of $18,521 per helicopter. Total costs per helicopter will vary, depending on whether repairs are needed. 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 helicopters 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 to the extent that it justifies making a regulatory distinction; 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.

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):
2012–14–14 Eurocopter Deutschland GmbH Helicopters: Amendment 39–17128; Docket No. FAA–2012–0356; Directorate Identifier 2011–SW–067–AD.
(a) Applicability

This AD applies to Model MBB–BK 117 A–3, MBB–BK 117 A–4, MBB–BK B–1, MBB– BK 117 B–2, and MBB–BK 117 C–1 helicopters with an external hoist system (hoist system) Part Number (P/N) 117–80403 or P/N 117–804061 installed, certificated in any category.
(b) Unsafe Condition

This AD defines the unsafe condition as an uncommanded cutting of the hoist cable.


### 44118 Federal Register / Vol. 77, No. 145 / Friday, July 27, 2012 / Rules and Regulations

This condition could result in loss of the helicopter hoist and load and subsequent injury to persons being lifted by the hoist.

(c) Effective Date

This AD becomes effective August 31,
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) Before the next hoist operation or within 30 days, whichever comes first, comply with either paragraph (1)(i), (1)(ii), or (1)(iii):

(i) Deactivate the hoist system by pulling the CABLE CUTTER, WINCH CONT, and WINCH BOOM circuit breakers and securing each circuit breaker with a cable tie; or

(ii) Deactivate the hoist system by removing the hoist boom from the helicopter;

or (iii) Deactivate the external hoist operator handle cable-cutter function by accomplishing the following:

(A) Modify the helicopter wiring and the operator handle, P/N 76803, in accordance with the Accomplishment Instructions, Paragraph 3.B.1 (b), of Eurocopter Emergency Alert Service Bulletin MBB–BK117–80–166, Revision 1, dated August 4, 2011 (ASB).

(B) Inspect the operator handle P/N 76803 and the coiled cable of the operator handle for damage in accordance with Paragraph 3.B.1.(a)(2) of the ASB. Damage is also defined as any condition that could prevent the part’s ability to perform its intended function.

(1) If the operator handle or the coiled cable of the operator handle has damage, replace the operator handle with an airworthy operator handle P/N 76803, before the next hoist operation.

(2) At intervals not to exceed 30 days, repeat the inspection in Paragraph (1)(iii)(B) of the Required Actions section of this AD.

(2) Before installing an affected hoist system on any helicopter, comply with Paragraph (1) of the Required Actions section of this AD.

(3) Before installing an operator handle P/N 76803 on any helicopter, comply with Paragraph (1)(iii)(A) of the Required Actions section of this AD.
(f) Alternative Methods of Compliance (AMOCs)

(1) The Manager, Safety Management Group, FAA, may approve AMOCs for this AD. Send your proposal to: George Schwab, Aviation Safety Engineer, Safety Management Group, Rotorcraft Directorate, FAA, 2601 Meacham Blvd., Fort Worth, TX 76137; telephone (817) 222–5110; email george.schwab@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 the European Aviation Safety Agency (EASA) AD No. 2011–0126, dated July 1, 2011; EASA AD No. 2011–0131, dated July 8, 2011; and EASA AD No. 2011–0148, dated August 5,
2011. (h) Subject

Joint Aircraft Service Component (JASC) Code: 2597, Equipment/furnishing system wiring.
(i) Material Incorporated by Reference

(1) The Director of the Federal Register approved the incorporation by reference 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 Emergency Alert Service Bulletin MBB–BK117–80–166, Revision 1, dated August 4, 2011.

(3) For 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 review the service information at the FAA, Office of the Regional Counsel, Southwest Region, 2601 Meacham Blvd., Room 663, Fort Worth, Texas 76137.

(5) You may also review a copy 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 NARA, call (202) 741–6030, or go
to: http://www.archives.gov/federal

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. Issued in Fort Worth, Texas, on July 11,
2012. Kim Smith, Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. 2012–17604 Filed 7–26–12; 8:45 am]

**BILLING CODE 4910–13–P**

**DEPARTMENT OF TRANSPORTATION**

**Federal Aviation Administration**

**14 CFR Part 39**

**[Docket No. FAA–2012–0766; Directorate Identifier 2012–SW–056–AD; Amendment**  **39–17133; AD 2012–15–04]**

**RIN 2120–AA64**

**Airworthiness Directives; Eurocopter France Helicopters** 

**AGENCY :**  Federal Aviation Administration (FAA), Department of Transportation (DOT). **ACTION :**  Final rule; request for
comments.

**SUMMARY :**  We are adopting a new airworthiness directive (AD) for Eurocopter France (Eurocopter) Model EC155B1 helicopters with a certain automated flight control system installed. This AD requires changing the minimum required crew for instrument flight rules (IFR) operations from one pilot to two. This AD is prompted by a report that an EC155B1 helicopter experienced significant intermittent roll oscillations while coupled to the autopilot. These actions are intended to decrease the pilot’s workload while experiencing any oscillations during landing, which could result in possible loss of control of the helicopter.

**DATES :**  This AD becomes effective August 13, 2012.

We must receive comments on this AD by September 25, 2012.

**ADDRESSES :**  You may send comments by any of the following methods:

• Federal eRulemaking Docket: Go to http://www.regulations.gov. Follow the online instructions for sending your comments electronically.

• Fax: 202–493–2251.

• Mail: Send comments to the U.S. Department of Transportation, Docket Operations, M–30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE., Washington, DC 20590–0001.

• Hand Delivery: Deliver to the ‘‘Mail’’ address between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays.

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 through Friday, except Federal holidays. The AD docket contains this AD, the economic evaluation, any comments received, and other information. The street address for the Docket Operations Office (telephone 800- 647–5527) is in the **ADDRESSES** section. Comments will be available in the AD docket shortly after receipt.

**FOR FURTHER INFORMATION CONTACT :**  Clark Davenport, Aviation Safety Engineer, Safety Management Group, Rotorcraft Directorate, FAA, 2601 Meacham Blvd., Fort Worth, Texas 76137; telephone (817) 222–5110; email clark.davenport@faa.gov.

**SUPPLEMENTARY INFORMATION :** 
Comments Invited

This AD is a final rule that involves requirements affecting flight safety, and we did not provide you with notice and