## 65166 Federal Register / Vol. 78, No. 211 / Thursday, October 31, 2013 / Rules and Regulations

Accomplishment Instructions, paragraphs 2.A through 2.C, of Erickson Service Bulletin No. 64B10–3, Revision D, dated October 15, 2007, except you are not required to contactErickson nor send hinge pins to them. A nondestructive testing (NDT) UT Level I Special, Level II, or Level III inspector who is qualified under the guidelines established byASNT SNT–TC–1A, ISO 9712, or an FAAaccepted equivalent qualification standard for NDT inspection and evaluation, must perform the UT inspection.

(5) Within 150 hours TIS or before reaching 1,450 hours TIS, whichever occurs later, perform a fluorescent-magnetic particle inspection (MPI) of each second stage planetary plate assembly, P/N 6435–20231– 016, for a crack.

(6) Within 150 hours TIS or before reaching 1,450 hours TIS, whichever occurs later, and thereafter at intervals not to exceed 650 hours TIS, perform an MPI of each M/R shaft, P/ N 6435–20078–104, for a crack, paying particular attention to the lower spline area.

(7) Within 150 hours TIS or before reaching 1,450 hours TIS, whichever occurs later, and thereafter at intervals not to exceed 1,450 hours TIS, perform an MPI of each M/R shaft, P/N 6435–20078–105, for a crack, paying particular attention to the lower spline area.

(8) Within 150 hours TIS or before reaching 3,375 hours TIS, whichever occurs later, and thereafter at intervals not to exceed 3,375 hours TIS, perform a fluorescent penetrant inspection of each housing lug on each servo housing, P/N S1565–20252–2, for a crack.

(9) At each overhaul of the main gearbox assembly, P/N 6435–20400–053, –054, –058,
–060, –062, –063, –064, –065, or –066, perform an MPI of the entire shaft of each M/R shaft assembly, P/N 6435–20078–014, –015, or –016, for a crack, paying particular attention to the rotating swashplate spherical bearing ball travel area, which is located approximately ten inches above the upper roller bearing journal shoulder.

(10) If there is a crack in any part, before further flight, replace the cracked part.

(11) At each overhaul of the damper assembly, P/N 6410–26200–042, replace the following parts with airworthy parts that have zero (0) hours TIS:

(i) All Air Force-Navy Aeronautical Standard (AN), Aerospace Standard (AS), Military Standard (MS), and National Aerospace Standard (NAS) nuts, bolts, washers, and packings, except packing, P/N MS28775–011, installed on stud, P/N SHF111–11SN–12A;

(ii) Lock washer, P/N SS5073–2; (iii) Nut, P/N SS5081–05; (iv) Felt seal, P/N S1510–26017; (v) Retaining ring, P/N UR106L; and (vi) Nut, P/N 6410–26214–101.

(g) Alternative Methods of Compliance (AMOCs)

(1) The Manager, Rotorcraft Certification Office, FAA, may approve AMOCs for this AD. Send your proposal to: Michael Kohner, Aerospace Engineer, Rotorcraft Certification Office, Rotorcraft Directorate, FAA, 2601 Meacham Blvd., Fort Worth, TX 76137; telephone (817) 222–5170; email 7-avs-asw170@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.

(h) Additional Information

Erickson Service Bulletin No. 64B General– 1, Revision 19, dated September 15, 2010, which is not incorporated by reference,
contains additional information about the subject of this AD. For service informationidentified in this AD, contact Erickson AirCrane Incorporated, ATTN: Chris Erickson, Director of Regulatory Compliance, 3100 Willow Springs Rd., P.O. Box 3247, Central Point, OR 97502, telephone (541) 664–5544, fax (541) 664–2312, email address cerickson@
ericksonaircrane.com. You may review a copy of this information at the FAA, Office of the Regional Counsel, Southwest Region, 2601 Meacham Blvd., Room 663, Fort Worth,

Texas 76137.

(i) Subject

Joint Aircraft Service Component (JASC) Code: 6200: Main Rotor System; 6300: Main Rotor Drive System; 6410: Tail Rotor Blades; 6500: Tail Rotor Drive System.

(j) 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) Erickson Service Bulletin No. 64B10–3, Revision D, dated October 15, 2007.

(ii) Reserved. (3) For Erickson service informationidentified in this AD, contact Erickson AirCrane Incorporated, ATTN: Chris Erickson, Director of Regulatory Compliance, 3100 Willow Springs Rd, P.O. Box 3247, Central Point, OR 97502, telephone (541) 664–5544, fax (541) 664–2312, email address cerickson@
ericksonaircrane.com.

(4) You may view this service information that is incorporated by reference at FAA, Office of the Regional Counsel, Southwest Region, 2601 Meacham Blvd., Room 663, Fort Worth, Texas 76137.

(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 September

25, 2013.
Lance T. Gant, Acting Directorate Manager, Rotorcraft Directorate, Aircraft Certification Service.

[FR Doc. 2013–24955 Filed 10–30–13; 8:45 am]

**BILLING CODE 4910–13–P** 

### DEPARTMENT OF TRANSPORTATION

**Federal Aviation Administration**

**14 CFR Part 39**

**[Docket No. FAA–2013–0625; Directorate Identifier 2013–NM–013–AD; Amendment**  **39–17638; AD 2013–22–06]**

**RIN 2120–AA64**



### Airworthiness Directives; The Boeing **Company Airplanes**

**AGENCY** 

### : Federal Aviation Administration (FAA), DOT.

**ACTION** 

### : Final rule.

**SUMMARY** 

### : We are superseding Airworthiness Directive (AD) 94–13–06 for certain The Boeing Company Model 747 series airplanes. AD 94–13–06 required repetitive detailed inspections to detect cracking in certain fuselage upper deck tension ties, repair or modification of any cracked tension ties, and repetitive inspections of repaired and modified tension ties and repair or modification if necessary. AD 94–13–06 also provided for optional terminating action for the repetitive detailed inspections of tension ties that had not been repaired or modified. This new AD retains the repetitive inspections, mandates the previously optional terminating modification, and adds, for tension ties that have not been repaired or modified, repetitive inspections that must be done concurrently with the existing repetitive inspections. This AD was prompted by an evaluation by the design approval holder indicating that the upper deck tension ties of the fuselage are subject to widespread fatigue damage. We are issuing this AD to prevent widespread fatigue damage of certain fuselage upper deck tension ties, which could result in reduced structural integrity of the airplane.

**DATES** 

### : This AD is effective December 5,

2013.

The Director of the Federal Register approved the incorporation by reference of a certain publication listed in this AD as of December 5, 2013.

**ADDRESSES** 

### : For service information identified in this AD, contact, contact Boeing Commercial Airplanes, Attention: Data & Services Management, P.O. Box 3707, MC 2H–65, Seattle, WA 98124–2207; telephone 206–544–5000, extension 1; fax 206–766–5680; Internet https://www.myboeingfleet.com. You may view this referenced service information at the FAA, Transport Airplane Directorate, 1601 Lind Ave. SW., Renton, Washington. For information on the availability of this material at the FAA, call 425–227–1221.


## 65167 Federal Register / Vol. 78, No. 211 / Thursday, October 31, 2013 / Rules and Regulations

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**

### : Nathan Weigand, Aerospace Engineer, Airframe Branch, ANM–120S, FAA, Seattle Aircraft Certification Office, 1601 Lind Avenue SW., Renton, Washington 98057–3356; phone: (425) 917–6428; fax: (425) 917–6590; email: nathan.p.weigand@faa.gov.

**SUPPLEMENTARY INFORMATION** 

### :

Discussion

We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 to supersede AD 94–13–06, Amendment 39–8946 (59 FR 32879, June 27, 1994). AD 94–13–06 applied to the specified products. The NPRM published in the Federal Register on July 22, 2013 (78 FR 43839). The NPRM proposed to continue to require repetitive detailed inspections to detect cracking in certain fuselage upper deck tension ties, repair or modification of any cracked tension ties, and repetitive inspections of repaired and modified tension ties and repair or modification if necessary. The NPRM also proposed to mandate the previously optional terminating modification, and add, for tension ties that have not been repaired or modified, repetitive inspections that must be done concurrently with the existing repetitive inspections.

Comments

We gave the public the opportunity to participate in developing this AD. We have considered the comment received. Boeing supported the NPRM (78 FR 43839, July 22, 2013).

Conclusion

We reviewed the relevant data, considered the comment received, and determined that air safety and the public interest require adopting this AD as proposed.

Costs of Compliance

We estimate that this AD affects 113 airplanes of U.S. registry.

We estimate the following costs to comply with this AD:



### E STIMATED 

### COSTS

Action Labor cost Parts cost Cost per product Cost on U.S. operators

Detailed inspections [retained action from AD

94–13–06, Amendment 39–8946 (59 FR 32879, June 27, 1994)]. 5 work-hours × $85 per hour = $425. $0 $425 per inspection cycle. $48,025 per inspection cycle.

Post-mod/repair inspections [new proposed action]. 1 work-hour × $85 per hour = $85. 0 $85 ............................... $9,605.

Modification [new proposed action] ..................... Up to 112 work-hours × $85 per hour = up to $9,520. 0 Up to $9,520 ................ Up to $1,075,760.



### We have received no definitive data that would enable us to provide cost
estimates for the on-condition actions specified in this AD.

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

We have determined that 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:

**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 removing Airworthiness Directive (AD) 94–13–06, Amendment 39–8946 (59 FR 32879, June 27, 1994), and adding the following new AD:

2013–22–06 The Boeing Company: Amendment 39–17638; Docket No. FAA–2013–0625; Directorate Identifier

2013–NM–013–AD.

(a) Effective Date

This AD is effective December 5, 2013.

(b) Affected ADs

This AD supersedes AD 94–13–06, Amendment 39–8946 (59 FR 32879, June 27, 1994).


## 65168 Federal Register / Vol. 78, No. 211 / Thursday, October 31, 2013 / Rules and Regulations

(c) Applicability

This AD applies to The Boeing Company Model 747–100, 747–200B, and 747–200F series airplanes, certificated in any category, as listed in Boeing Alert Service Bulletin 747–53A2371, Revision 2, dated December
11, 2012.

(d) Subject

Joint Aircraft System Component (JASC)/ Air Transport Association (ATA) of America Code 53, Fuselage.

(e) Unsafe Condition

This AD was prompted by an evaluation by the design approval holder indicating that the upper deck tension ties of the fuselage are subject to widespread fatigue damage. We are issuing this AD to prevent widespread fatigue damage of certain fuselage upper deck tension ties, which could result in reduced structural integrity of the airplane.

(f) Compliance

Comply with this AD within the compliance times specified, unless already
done.

(g) Inspections and Repair/Modification

Except as required by paragraph (k)(3) of this AD, at the applicable time specified in Tables 1 and 3 of paragraph 1.E., ‘‘Compliance’’ of Boeing Alert Service Bulletin 747–53A2371, Revision 2, dated December 11, 2012: Do detailed and surface high frequency eddy current (HFEC) inspections for cracks in the tension ties, as applicable, and do all applicable corrective actions, in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 747–53A2371, Revision 2, dated December 11, 2012, except as required by paragraph (k)(2) of this AD. The effective date of AD 94–13–06, Amendment 39–8946 (59 FR 32879, June 27, 1994) is July 27, 1994. Do all applicable corrective actions before further flight. Repeat the detailed and HFEC inspections thereafter at the time specified in paragraph 1.E., ‘‘Compliance,’’ of Boeing Alert Service Bulletin 747–53A2371, Revision 2, dated December 11, 2012, except as specified in paragraph (k)(1) of this AD. Repair of a tension tie, in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 747–53A2371, Revision 2, dated December 11, 2012, except as required by paragraph (k)(2) of this AD, terminates the requirements of this paragraph for that tension tie only.

(h) Modification

Except as provided by paragraph (k)(3) of this AD, at the applicable time specified in Table 3 of paragraph 1.E., ‘‘Compliance,’’ of Boeing Alert Service Bulletin 747–53A2371, Revision 2, dated December 11, 2012: Modifythe tension ties, including doing an openhole HFEC inspection for cracks before enlarging the hole, in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 747–53A2371, Revision 2, dated December 11, 2012. Modification of the tension ties terminates the requirements of paragraph (g) of this AD. If any cracking is found, before further flight, do the repair using a method approved in accordance with the procedures specified in paragraph (l) of this AD.

(i) Post-Repair/Modification Inspections

At the applicable time specified in Table 2 of paragraph 1.E., ‘‘Compliance,’’ of Boeing Alert Service Bulletin 747–53A2371, Revision 2, dated December 11, 2012: Do a detailed inspection of all repaired and modified tension ties, and do all applicable corrective actions, except as required by paragraph (k)(2) of this AD, in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 747–53A2371, Revision 2, dated December 11, 2012, except as required by paragraph (k)(2) of this AD. Repeat the inspection thereafter at the times specified in paragraph 1.E., ‘‘Compliance,’’ of Boeing Alert Service Bulletin 747–53A2371, Revision 2, dated December 11, 2012. Do all applicable corrective actions before further flight.

(j) Credit for Previous Actions

This paragraph provides credit for the modification required by paragraphs (g) and (h) of this AD if that modification was done before the effective date of this AD using Boeing Service Bulletin 747–53–2371, dated July 29, 1993; or Boeing Service Bulletin 747–53–2371, Revision 1, dated April 27, 1995; which are not incorporated by reference in this AD. Boeing Service Bulletin 747–53–2371, dated July 29, 1993, was incorporated by reference in AD 94–13–06, Amendment 39–8946 (59 FR 32879, June 27, 1994).

(k) Exception to Service Information

(1) Where Row 2 of Table 3 of paragraph 1.E., ‘‘Compliance,’’ of Boeing Alert Service Bulletin 747–53A2371, Revision 2, dated December 11, 2012, specifies repeating a ‘‘detailed’’ inspection, ‘‘as given in Part 4’’ of this service information, the repetitive inspections required by this AD are ‘‘HFEC’’ inspections, done in accordance with Part 4 and Figure 8 of Boeing Alert Service Bulletin 747–53A2371, Revision 2, dated December
11, 2012.

(2) Where Boeing Alert Service Bulletin 747–53A2371, Revision 2, dated December 11, 2012, specifies contacting Boeing for repair instructions, or does not include repair instructions for a crack found in an area other than the aft tension tie area: Before further flight, do the repair using a method approved in accordance with the procedures specified in paragraph (l) of this AD.

(3) Where Boeing Alert Service Bulletin 747–53A2371, Revision 2, dated December 11, 2012, specifies a compliance time of ‘‘after the Revision 2 date of this service bulletin,’’ this AD requires compliance within the specified compliance time after the effective date of this AD.

(l) Alternative Methods of Compliance (AMOCs)

(1) The Manager, Seattle Aircraft Certification Office (ACO), 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 paragraph (m)(1) of this AD. Information may
be emailed to: 9-ANM-Seattle-ACO-AMOCRequests@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 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.

(4) AMOCs approved for AD 94–13–06, Amendment 39–8946 (59 FR 32879, June 27, 1994), are approved as AMOCs for the corresponding actions required by paragraphs (g), (h), and (i) of this AD.

(m) Related Information

(1) For more information about this AD, contact Nathan Weigand, Aerospace Engineer, Airframe Branch, ANM–120S, FAA, Seattle Aircraft Certification Office, 1601 Lind Avenue SW., Renton, Washington 98057–3356; phone: (425) 917–6428; fax: (425) 917–6590; email: nathan.p.weigand@ faa.gov.

(2) Service information in this AD that is not incorporated by reference may be obtained at the addresses specified in paragraphs (n)(3) and (n)(4) of this AD.

(n) 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 Alert Service Bulletin 747– 53A2371, Revision 2, dated December 11,

2012.

(ii) Reserved. (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; telephone 206– 544–5000, extension 1; fax 206–766–5680;

Internet https://www.myboeingfleet.com.

(4) You may view this service information at 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 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.


## 65169 Federal Register / Vol. 78, No. 211 / Thursday, October 31, 2013 / Rules and Regulations

Issued in Renton, Washington, on October
15, 2013. Jeffrey E. Duven, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service.

[FR Doc. 2013–25307 Filed 10–30–13; 8:45 am]

**BILLING CODE 4910–13–P**



### DEPARTMENT OF TRANSPORTATION

**Federal Aviation Administration**

**14 CFR Part 39**

**[Docket No. FAA–2013–0446; Directorate Identifier 2010–SW–007–AD; Amendment**  **39–17629; AD 2013–21–05]**

**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 (Eurocopter) Model EC135 P1, P2, P2+, T1, T2, and T2+ helicopters. This AD requires inspecting each linear transducer bearing (bearing) for freedom of movement and replacing the bearing if there is binding or rough turning or if there is chafing or damage on the lower side of the floor. Also, this AD requires modifying and re-identifying a certain rod. This AD was prompted by an incident involving limited control of a tail rotor because of the binding of a bearing. The actions of this AD are intended to detect and replace each bearing subject to binding, which could lead to subsequent loss of control of the helicopter.

**DATES** 

### : This AD is effective December 5,

2013.

The Director of the Federal Register approved the incorporation by reference of a certain document listed in this AD as of December 5, 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**

### : Matt Fuller, Senior Aviation Safety Engineer, Safety Management Group, Rotorcraft Directorate, FAA, 2601 Meacham Blvd., Fort Worth, Texas 76137; telephone (817) 222–5110; email matthew.fuller@ faa.gov.

**SUPPLEMENTARY INFORMATION** 

### :

Discussion

On May 23, 2013, at 78 FR 30793, the Federal Register published our notice of proposed rulemaking (NPRM), which proposed to amend 14 CFR part 39 by adding an AD that would apply to Model EC135 P1, P2, P2+, T1, T2, and T2+ helicopters, with bearing, part number (P/N) LN9367GE6N2; rod, P/N L671M5040205; lever, P/N L671M5040101; and floor, P/N L533M1014101, L533M1014102, L533M1014103, L533M1014104, L533M1014105 or L533M1014106, installed. The NPRM proposed to require, at specified intervals, inspecting each bearing for freedom of movement. The NPRM also proposed, before further flight, if there is binding or rough turning, replacing the bearing or if there is chafing or damage on the lower side of the floor, replacing the bearing and repairing the floor, and, thereafter, installing a Teflon strip. The NPRM also proposed modifying the rod and re-identifying the rod and lever with a new part number. The requirements were intended to detect and replace each bearing subject to binding, which could lead to subsequent loss of control of the helicopter.

The NPRM was prompted by AD No. 2006–0318 R1, dated October 27, 2006, issued by the European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Union, to correct an unsafe condition for all Eurocopter Model EC 135 helicopters. EASA advises of an incident in which impaired control of an EC 135 tail rotor was detected. EASA states that according to examinations, the bearing of the linear transducer was subject to binding, which limited the control range.

FAA’s Determination

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 30793, May 23, 2013).

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 its 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.

Differences Between This AD and the
EASA AD

This AD does not refer to the compliance date of October 31, 2006, because that date has passed; instead we require compliance within 100 hours time-service (TIS). This AD does not require contacting Eurocopter customer support. This AD requires modifying each rod within 100 hours TIS, rather than within 800 hours TIS as specified in the EASA AD.

Related Service Information

Eurocopter has issued Alert Service Bulletin EC135–67A–012, Revision 1, dated October 18, 2006 (ASB), which specifies inspecting the bearing of the linear transducer for freedom of movement and the lower side of the floor for chafing or damage. If there is binding, the ASB specifies replacing the bearing. If there is chafing or damage on the floor, the ASB specifies replacing the bearing and repairing the floor. The ASB also specifies modifying and reidentifying a certain rod. EASA classified this ASB as mandatory and issued EASA AD 2006–0318 R1, dated October 27, 2006, to ensure the continued airworthiness of these helicopters.

Costs of Compliance

We estimate that this AD will affect 214 helicopters of U.S. Registry. We estimate that operators may incur the following costs in order to comply withthis AD: It will take about 10 workhours to inspect the bearing for freedom of movement at an average labor rate of