### 52407 Federal Register / Vol. 78, No. 164 / Friday, August 23, 2013 / Rules and Regulations

(a) Effective Date

This airworthiness directive (AD) becomes effective September 27, 2013.

(b) Affected ADs

None.

(c) Applicability

This AD applies to Airbus Model A330–

301, –302, –303, –321, –322, –323, –341, –342, and –343 airplanes; and Model A340– 211, –212, –213, –311, –312, and –313 airplanes; certificated in any category; all manufacturer serial numbers; if fitted with a
trimmable horizontal stabilizer actuator (THSA) having part number (P/N) 47147–500
or P/N 47147–700.

(d) Subject

Air Transport Association (ATA) of America Code 27, Flight Controls.

(e) Reason

This AD was prompted by a determination that ballscrew rupture could occur on certain THSAs. We are issuing this AD to detect and correct ballscrew rupture, which, along with corrosion on the ballscrew lower splines, may lead to loss of transmission of THSA torque loads from the ballscrew to the tie-bar and consequent THSA blowback, which could result in loss of control of the airplane.

(f) Compliance

You are responsible for having the actions required by this AD performed within the compliance times specified, unless the actions have already been done.

(g) Repetitive Integrity Tests

At the later of the times specified in paragraph (g)(1) or (g)(2) of this AD, as applicable, do a THSA ballscrew shaft integrity test, in accordance with the Accomplishment Instructions of Airbus Mandatory Service Bulletin A330–27–3191, dated June 7, 2012; or Airbus Mandatory Service Bulletin A340–27–4186, dated June 7, 2012; as applicable. Repeat the integrity
test thereafter at intervals not to exceed 12,000 flight hours or 4,400 flight cycles,
whichever occurs first.

(1) At the latest of the times specified in paragraph (g)(1)(i), (g)(1)(ii), or (g)(1)(iii) of
this AD.

(i) Within 12,000 flight hours since the airplane’s first flight; or

(ii) Within 12,000 flight hours since the most recent THSA ballscrew shaft integrity test was done as specified in maintenance review board report (MRBR) Task 274000–12;

or (iii) Within 12,000 flight hours since the most recent THSA ballscrew shaft integrity test was done, as specified in Airbus Mandatory Service Bulletin A330–27–3179 or Airbus Mandatory Service Bulletin A340– 27–4175, as applicable. (These service bulletins specify testing in case of type II or type III findings).

(2) Within 1,000 flight hours after the effective date of this AD, but without exceeding the latest of the times specified in paragraph (g)(2)(i), (g)(2)(ii), or (g)(2)(iii) of
this AD.

(i) 16,000 flight hours since the airplane’s first flight. (ii) 16,000 flight hours since the most recent THSA ballscrew shaft integrity test was done, as specified in MRBR task 274000–

12.

(iii) 16,000 flight hours since the most recent THSA ballscrew shaft integrity test was done, as specified in Airbus Mandatory Service Bulletin A330–27–3179, or Airbus Mandatory Service Bulletin A340–27–4175, as applicable. (These service bulletins specify testing in case of type II or type III findings).

(h) Replacement

If the result from any test required by paragraph (g) of this AD is not correct, as specified in the Accomplishment Instructions of Airbus Mandatory Service Bulletin A330–27–3191, dated June 7, 2012; or Airbus Mandatory Service Bulletin A340– 27–4186, dated June 7, 2012; as applicable: Before further flight, replace the THSA with a serviceable THSA, in accordance with the Accomplishment Instructions of Airbus Mandatory Service Bulletin A330–27–3191, dated June 7, 2012; or Airbus Mandatory Service Bulletin A340–27–4186, dated June 7, 2012; as applicable. Replacement of a THSA, as required by this paragraph, with a THSA having P/N 47147–500 or P/N 47147– 700, is not terminating action for the repetitive tests required by paragraph (g) of
this AD.

(i) Other FAA AD Provisions

The following provisions also apply to this

AD:

(1) Alternative Methods of Compliance (AMOCs): The Manager, International Branch, ANM–116, Transport Airplane Directorate, 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 International Branch, send it to ATTN: Vladimir Ulyanov, Aerospace Engineer, International Branch, ANM–116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, Washington 98057– 3356; telephone (425) 227–1138; fax (425) 227–1149. Information may be emailed to: 9- ANM-116-AMOC-REQUESTS@faa.gov. 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. The AMOC approval letter must specifically reference
this AD.

(2) Airworthy Product: For any requirement in this AD to obtain corrective actions from a manufacturer or other source, use these actions if they are FAA-approved. Corrective actions are considered FAA-approved if they are approved by the State of Design Authority (or their delegated agent). You are required to assure the product is airworthy before it
is returned to service.

(j) Related Information

Refer to Mandatory Continuing Airworthiness Information European Aviation Safety Agency Airworthiness Directive 2012–0210, dated October 11, 2012, for related information, which can be found in the AD docket on the internet at http:// www.regulations.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) Airbus Mandatory Service Bulletin A330–27–3191, dated June 7, 2012.

(ii) Airbus Mandatory Service Bulletin A340–27–4186, dated June 7, 2012.

(3) For service information identified in this AD, contact Airbus SAS, Airworthiness Office—EAL, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61 93 45 80; email airworthiness.A330-A340@airbus.com;

Internet http://www.airbus.com.

(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 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 August

1, 2013. Jeffrey E. Duven, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service.

[FR Doc. 2013–19161 Filed 8–22–13; 8:45 am]

**BILLING CODE 4910–13–P**

**DEPARTMENT OF TRANSPORTATION**

**Federal Aviation Administration**

**14 CFR Part 39**

**[Docket No. FAA–2013–0341; Directorate Identifier 2012–SW–025–AD; Amendment**  **39–17557; AD 2013–16–19]**

**RIN 2120–AA64**

**Airworthiness Directives; Eurocopter France Helicopters** 

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

**ACTION :**  Final rule.

**SUMMARY :**  We are adopting a new airworthiness directive (AD) for Eurocopter France (Eurocopter) Model EC120B and EC130B4 helicopters with a certain emergency flotation gear (float) installed. This AD requires inspecting the float for chafing of the fabric covering and adding protectors to the float installation to prevent contact between the float and the protruding


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sections of the installation. This AD was prompted by a report of a float that would not inflate during overhaul because one of the float compartments was punctured due to chafing. The
actions of this AD are intended to prevent failure of float and subsequent loss of control of the helicopter during an emergency water landing.

**DATES :**  This AD is effective September

27, 2013.

The Director of the Federal Register approved the incorporation by reference
of certain documents listed in this AD as of September 27, 2013.

**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, the foreignauthority’s AD, any incorporated-byreference 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 :**  Gary Roach, Aviation Safety Engineer, Regulations and Policy Group, Rotorcraft Directorate, FAA, 2601 Meacham Blvd., Fort Worth, Texas 76137; telephone (817) 222–5110; email gary.b.roach@faa.gov.

**SUPPLEMENTARY INFORMATION :** 

Discussion

On April 15, 2013, at 78 FR 22213, 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 Eurocopter Model EC120B helicopters with a left-hand (LH) emergency flotation gear, part number (P/N)

215674–0, 215674–1, or 215674–2 installed, fitted with a float, P/N 215481–0; or with a right-hand (RH) emergency flotation gear, P/N 215675–0, 215675–1, or 215675–2 installed, fitted with a float, P/N 215482–0; and Model EC130B4 helicopters with a LH emergency flotation gear P/N 217227–0 installed, fitted with a float P/N 217174–0; or with a RH emergency flotation gear P/N 217228–0 installed, fitted with a float, P/N 217195–0. The NPRM proposed to require inspecting the float for chafing of the fabric covering and adding protectors to the float installation to prevent contact between the float and the protruding
sections of the installation. The proposed requirements were intended to prevent failure of float and subsequent loss of control of the helicopter during an emergency water landing.

The NPRM was prompted by AD No. 2011–0185, dated September 23, 2011 (AD 2011–0185), issued by the European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European
Union. EASA issued AD 2011–0185 to
correct an unsafe condition for Eurocopter Model EC120 and EC130 helicopters. EASA advises that during overhaul of an emergency flotation gear installation, it was impossible to inflate the RH float according to the instructions in the equipment
manufacturer’s manual. An investigation revealed that one of the compartments in the float was punctured and several areas of the LH and RH floats were damaged, caused by chafing between the float and the protruding sections of the supply bars and banjo unions. To address this potentially unsafe condition, EASA issued AD No. 2009–0190, dated August 26, 2009 (AD 2009–0190), which required repetitive inspections of the floats to detect chafing. Aerazur, the float manufacturer, later developed protectors to be installed on the floats to
eliminate interference between the float and the blunt parts of the installation. EASA then issued AD 2011–0185, which superseded AD 2009–0190 and required installation of the protectors on the floats as terminating action for the repetitive inspections.

Comments

We gave the public the opportunity to participate in developing this AD, but we did not receive any comments on the NPRM (78 FR 22213, April 15, 2013).

FAA’s Determination

These helicopters have been approved by the aviation authority of France and are approved for operation in the United
States. Pursuant to our bilateral agreement with France, 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

Related Service Information

Eurocopter has issued Alert Service Bulletin (ASB) No. 05A011, Revision 0, dated June 8, 2009 (ASB 05A011), for Model EC120B helicopters and ASB No. 05A008, Revision 0, dated June 8, 2009 (ASB 05A008), for Model EC130B4 helicopters. Both ASBs specify inspecting the floats for deterioration and chafing at specified intervals and, if necessary, repairing the floats.

Eurocopter has also issued ASB No. EC120–25A026, Revision 0, dated July 11, 2011 (ASB EC120–25A026), for Model EC120B helicopters and ASB No. EC130–25A042, Revision 0, dated July 11, 2011 (ASB EC130–25A042), for Model EC130B4 helicopters. Both ASBsspecify modifying certain partnumbered LH and RH emergency flotation gear by adding protectors onto the rear bracket and supply couplings of the float installation. The ASBs specify following procedures in Aerazur Service Bulletin (SB) No. 25–69–87, dated March 14, 2011, for floats installed on Model EC120B helicopters and Aerazur SB No. 25–69–58, dated March 14, 2011,
for floats installed on Model EC130B4 helicopters. Each Aerazur SB is incorporated as an appendix to the corresponding Eurocopter ASB.

Costs of Compliance

We estimate that this AD will affect 60 helicopters of U.S. Registry. Based onan average labor rate of $85 per workhour, we estimate that operators may incur the following costs to comply with this AD. Inspecting the floats for chafing will require about .5 hour, for a cost per helicopter of $43, and a cost to U.S. operators of $2,580. Modifying the floats with protective covers will require about 1 hour and required parts cost about $500, for a cost per helicopter of $585, and a cost to U.S. operators of $35,100. The total estimated cost of this AD is $628 per helicopter and $37,680 for the U.S. operator fleet.

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


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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): 2013–16–19 Eurocopter France: Amendment 39–17557; Docket No. FAA–2013–0341; Directorate Identifier

2012–SW–025–AD.

(a) Applicability

(1) This AD applies to the following helicopters, certificated in any category:

(i) Model EC120B helicopters with a lefthand (LH) emergency flotation gear, part number (P/N) 215674–0, 215674–1, or 215674–2 installed, fitted with a float, P/N 215481–0; or with a right-hand (RH) emergency flotation gear, P/N 215675–0, 215675–1, or 215675–2 installed, fitted with a float, P/N 215482–0; and

(ii) Model EC130B4 helicopters with a LH emergency flotation gear P/N 217227–0 installed, fitted with a float P/N 217174–0; or with a RH emergency flotation gear P/N 217228–0 installed, fitted with a float, P/N

217195–0.

(b) Unsafe Condition

This AD defines the unsafe condition as chafing of the float due to contact with the protruding sections of the supply bars and banjo sections of the emergency flotation gear
installation. This condition could result in the float becoming punctured, failure of the float to inflate, and subsequent loss of control of the helicopter during an emergency water landing.

(c) Effective Date

This AD becomes effective September 27,

2013.

(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) For emergency flotation gear that have
accumulated 250 or more hours time-in service (TIS), within 50 hours TIS, accomplish the following:

(i) Undo the Velcro tapes and remove the break laces. Remove the caps from the cover
end. Unfold the cover.

(ii) Inspect each float area in contact with the emergency flotation gear protruding parts (supply bar, banjo union, and fittings) for chafing as shown in Figure 1 of Eurocopter Alert Service Bulletin (ASB) No. 05A011, Revision 0, dated June 8, 2009, or Eurocopter ASB No. 05A008, Revision 0, dated June 8, 2009, as appropriate for your model helicopter.

(iii) If there is any chafing between the protruding parts and the float fabric, before further flight, inspect the flotation gear.

(A) Unfold and visually inspect the float assemblies for any cuts, tears, punctures, or abrasion. Replace the cover if the internal polycarbonate sheet is cut or if the cover is cut or punctured.

(B) Lightly inflate the floats to approximately 50 hectopascals through the manual inflating valve and inspect the fabric panels and girts for any cuts, tears, punctures, or abrasion. If there is a cut, tear, puncture, or any abrasion, repair the float.

(2) For emergency floatation gear that have accumulated less than 250 hours TIS, on or before accumulating 300 hours TIS, inspect the float gear as described in paragraph (e)(1)(i) through (iii) of this AD.

(3) Within 300 hours TIS: (i) For Model EC120B helicopters, install protectors on and re-identify the P/N of each LH and RH emergency floatation gear as described in the Operating Instructions, paragraph 2.C., of Aerazur Service Bulletin (SB) No. 25–69–87, dated March 14, 2011. The Aerazur SB is attached as an appendix to Eurocopter Alert Service Bulletin (ASB) No. EC120–25A026, Revision 0, dated July

11, 2011.

(ii) For Model EC130B4 helicopters, install protectors on and re-identify the P/N of each LH and RH emergency floatation gear as described in the Operating Instructions, paragraph 2., of Aerazur SB No. 25–69–58, dated March 14, 2011. The Aerazur SB is attached as an appendix to Eurocopter ASB No. EC130–25A042, Revision 0, dated July

11, 2011.

(f) Alternative Methods of Compliance (AMOCs)

(1) The Manager, Safety Management Group, FAA, may approve AMOCs for this AD. Send your proposal to: Gary Roach, Aviation Safety Engineer, Regulations and Policy Group, Rotorcraft Directorate, FAA, 2601 Meacham Blvd., Fort Worth, Texas 76137; telephone (817) 222–5110; email gary.b.roach@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

(1) The subject of this AD is addressed in European Aviation Safety Agency AD No. 2011–0185, dated September 23, 2011, which
can be found in the AD Docket on the

Internet at http://www.regulations.gov.

(2) Eurocopter ASB No. EC120–25A026, Revision 0, dated July 11, 2011, and Eurocopter ASB No. EC130–25A042, Revision 0, dated July 11, 2011, which are not incorporated by reference, contain additional information about the subject of this AD. You may view this service information at the 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.

(h) Subject

Joint Aircraft Service Component (JASC) Code: 3212: Emergency Flotation Section.

(i) 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.


### 52410 Federal Register / Vol. 78, No. 164 / Friday, August 23, 2013 / Rules and Regulations

(i) Aerazur SB No. 25–69–58, dated March 14, 2011, which is attached as an appendix to Eurocopter ASB No. EC130–25A042, Revision 0, dated July 11, 2011.

(ii) Aerazur SB No. 25–69–87, dated March 14, 2011, which is attached as an appendix to Eurocopter ASB No. EC120–25A026, Revision 0, dated July 11, 2011.

(iii) Eurocopter ASB No. 05A008, Revision 0, dated June 8, 2009.

(iv) Eurocopter ASB No. 05A011, Revision 0, dated June 8, 2009.

(3) For Eurocopter and Aerazur 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 that is incorporated by reference in the AD
Docket on the Internet at http:// www.regulations.gov.

(5) You may also 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 August 2,

2013.
Lance T. Gant, Acting Directorate Manager, Rotorcraft Directorate, Aircraft Certification Service.

[FR Doc. 2013–19438 Filed 8–22–13; 8:45 am]

**BILLING CODE 4910–13–P**

**DEPARTMENT OF TRANSPORTATION**

**Federal Aviation Administration**

**14 CFR Part 39**

**[Docket No. FAA–2012–0887; Directorate Identifier 2009–SW–02–AD; Amendment 39–**  **17551; AD 2013–16–13]**

**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 Eurocopter Deutschland GmbH (ECD) Model BO–105A, BO–105C, BO–105S, BO–105LS A–1, BO–105LS A–3, MBB– BK 117 A–1, MBB–BK 117 A–3, MBB– BK 117 A–4, MBB–BK 117 B–1, MBB– BK–117 B–2, and MBB–BK 117 C–1 helicopters to require inspections for corrosion or thread damage to each tail rotor balance weight (weight) and each tail rotor control lever (lever). This AD was prompted by a European Aviation Safety Agency (EASA) AD and a Transport Canada Civil Aviation (TCCA) AD, both issued based on a report that corrosion was detected on a weight in
the area of the attachment thread on a model BO–105 helicopter. The actions
of this AD are intended to detect corrosion and thread damage in the threaded area of the weight and lever, and to prevent failure of a weight or lever, separation of tail rotor parts, severe vibration, and subsequent loss of control of the helicopter.

**DATES :**  This AD is effective September

27, 2013.

The Director of the Federal Register approved the incorporation by reference
of certain documents listed in this AD as of September 27, 2013.

**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, TX 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, the EASA andTCCA ADs, any incorporated-byreference 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 :**  Sharon Miles, Aviation Safety Engineer, Regulations and Policy Group, Rotorcraft Directorate, FAA, 2601 Meacham Blvd., Fort Worth, TX 76137; telephone (817) 222–5110; email sharon.y.miles@faa.gov.

**SUPPLEMENTARY INFORMATION :** 

Discussion

On August 29, 2012, at 77 FR 52265, 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 BO–105A, BO–105C, BO– 105S, BO–105LS A–1, BO–105LS A–3, MBB–BK 117 A–1, MBB–BK 117 A–3, MBB–BK 117 A–4, MBB–BK117 B–1, MBB–BK 117 B–2, and MBB–BK 117 C– 1 helicopters with certain levers and weights installed. The NPRM proposed to require conducting repetitive visual inspections of each weight and lever and proposed procedures for installing a weight or lever. Additionally, the NPRM proposed allowable tolerances for corrosion or thread damage on the threaded portion of a weight or lever and proposed to require that a part with corrosion or mechanical damage in
excess of allowable tolerances be replaced with an airworthy part. The proposed requirements were intended to detect corrosion and thread damage in the threaded area of a weight or lever, to prevent failure of a weight or lever, separation of tail rotor parts, severe vibration, and subsequent loss of control of the helicopter.

The NPRM was prompted by AD No. 2008–0206, dated November 25, 2008, issued by EASA, which is the Technical Agent for the Member States of the European Union, and AD No. CF–2009– 12, dated March 24, 2009, issued by the TCCA, which is the aviation authority
for Canada. EASA issued AD No. 2008–
0206 to correct the unsafe condition for ECD Model BO 105 A, BO 105 C, BO 105 LS A–1, BO 105 D, BO 105 DS, BO 105 DB, BO 105 DBS, BO 105 DB–4, BO 105 DBS–4, BO 105 DBS–5, BO 105 S, MBB–BK 117 A–1, MBB–BK 117 A–3, MBB–BK 117 A–4, MBB–BK 117 B–1, MBB–BK 117 B–2, and MBB–BK 117 C– 1 helicopters. The TCCA issued AD No.
CF–2009–12 to correct the unsafe condition for Eurocopter Model BO 105 LS A–3 helicopters. These ADs state that during a periodical inspection, corrosion was detected on the weights
in the area of the attachment thread. Since the issuance of the Canadian AD, the type certificate for the Model BO
105 LS A–3 has been transferred from Eurocopter Canada Limited to Eurocopter Deutschland (Germany).

Comments

We gave the public the opportunity to participate in developing this AD, but we did not receive any comments on the NPRM (77 FR 52265, August 29, 2012).

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