### 3316 Federal Register / Vol. 81, No. 13 / Thursday, January 21, 2016 / Rules and Regulations

telephone +44(0)2890–462469; fax +44(0)2890 468444; email michael.mulholland@aero.bombardier.com;
Internet http://www.bombardier.com

.

(5) You may view this 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.

(6) 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 January
4, 2016. Victor Wicklund, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service.

[FR Doc. 2016–00378 Filed 1–20–16; 8:45 am]

**BILLING CODE 4910–13–P**

**DEPARTMENT OF TRANSPORTATION**

**Federal Aviation Administration**

**14 CFR Part 39**

**[Docket No. FAA–2015–1422; Directorate Identifier 2014–NM–125–AD; Amendment**  **39–18370; AD 2016–01–11]**

**RIN 2120–AA64**

**Airworthiness Directives; Airbus Airplanes** 

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

**ACTION :**  Final rule.

**SUMMARY :**  We are superseding Airworthiness Directive (AD) 98–18–26, for certain Airbus Model A320 series airplanes. AD 98–18–26 required repetitive inspections to detect fatigue cracking of the front spar vertical stringers on the wings; and repair, if necessary. This new AD requires repetitive high frequency eddy current (HFEC) inspections for cracking of the radius of the front spar vertical stringers and the horizontal floor beam on frame 36, a rototest inspection for cracking of the fastener holes of the front spar vertical stringers on frame 36, and repair if necessary. This AD was prompted by reports that indicate new repetitive inspections having new thresholds and intervals are needed and that additional work is needed to accomplish the inspections on airplanes on which a previous modification has been accomplished. We are issuing this AD to detect and correct fatigue cracking of the front spar vertical stringers on the wings, which could result in the reduced structural integrity of the airframe.

**DATES :**  This AD becomes effective February 25, 2016.

The Director of the Federal Register approved the incorporation by reference of a certain publication listed in this AD as of February 25, 2016.

**ADDRESSES :**  You may examine the AD docket on the Internet at http:// www.regulations.gov/ #!docketDetail;D=FAA-2015-1422; or in person at the Docket 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.

For service information identified in this AD, contact Airbus, Airworthiness Office—EIAS, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61 93 44 51; email account.airwortheas@airbus.com; Internet http:// www.airbus.com . You may view this referenced 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. It is also available on the Internet

at http://www.regulations.gov by searching for and locating Docket Number FAA–2015–1422.

**FOR FURTHER INFORMATION CONTACT :**  Sanjay Ralhan, Aerospace Engineer, International Branch, ANM–116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057–3356; telephone 425–227–1405; fax 425–227–1149.

**SUPPLEMENTARY INFORMATION :** 

Discussion

We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 to supersede AD 98–18–26, Amendment 39–10742 (63 FR 47423, September 8, 1998). AD 98–18–26 applied to certain Airbus Model A320 series airplanes. The NPRM published in the Federal Register on June 5, 2015 (80 FR 32063).

The European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Union, has issued EASA Airworthiness Directive 2014–0069, dated March 19, 2014 (referred to after this as the Mandatory Continuing Airworthiness Information, or ‘‘the MCAI’’), to correct an unsafe condition on certain Airbus Model A320–211, –212, and –231 airplanes. The MCAI states:

During center fuselage certification full scale fatigue test, cracks were found on the front vertical stringer at frame 36. Analysis of these findings indicated that a number of inservice aeroplanes could be similarly affected.

This condition, if not detected and corrected, could lead to crack propagation and consequent deterioration of the structural integrity of the aeroplane.

To address this potential unsafe condition, [Directorate General for Civil Aviation] DGAC France AD 97–311–105 [which corresponds to FAA AD 98–18–26, Amendment 39–10742 (63 FR 47423, September 8, 1998)] was issued to require repetitive [HFEC] inspections [for cracking] in accordance with the instruction of Airbus Service Bulletin (SB) A320–57–1016. At the same time, the modification provided by Airbus SB A320–57–1017 was considered to be terminating action for the repetitive inspections required by DGAC France AD

97–311–105.

Since that [DGAC] AD was issued, and following new analysis, modification per Airbus SB A320–57–1017 is no longer considered to be terminating action for the repetitive inspections as required by DGAC
France AD 97–311–105.

Aeroplanes with [manufacturer serial number] MSN 0080 up to 0155 inclusive have been delivered with the addition of a 5 [millimeter] mm thick light alloy shim under the heads of 2 fasteners at the top end of the front spar vertical stringers (Airbus modification 21290P1546, which is the production line equivalent to in-service modification through Airbus SB A320–57– 1017). From MSN 0156 and higher, all aeroplanes are delivered with vertical stiffeners of the forward wing spar upper end with stiffener cap thickness increased from 4 to 6 mm (Airbus modification 21290P1547).

Prompted by these findings, Airbus issued SB A320–57–1178 to introduce new repetitive inspections with new thresholds and intervals.

For the reasons described above, DGAC France AD 97–311–105 is superseded and this [EASA] AD requires the repetitive inspections at new thresholds and intervals.

After EASA issued [proposed airworthiness directive] PAD 14–021, it was discovered that additional work [HFEC inspections for cracking of the radius of spar vertical stringers and horizontal beam in the center fuselage of frame 36, and a rototest inspection for cracking of the fastener holes of the spar vertical stringers radius on Frame 36 and repair if necessary], to be included in Revision 01 of Airbus SB A320–57–1178, is required to accomplish the inspections. This Final [EASA] AD has been amended accordingly.

You may examine the MCAI in the AD docket on the Internet at http:// www.regulations.gov/ #!documentDetail;D=FAA-2015-1422-

0002

. Comments

We gave the public the opportunity to participate in developing this AD. The following presents the comments received on the NPRM (80 FR 32063, June 5, 2015) and the FAA’s response to the comments.


### 3317 Federal Register / Vol. 81, No. 13 / Thursday, January 21, 2016 / Rules and Regulations

Requests for Clarification of Certain Requirements

Delta Airlines (DAL) asked that we move the repetitive inspection intervals from paragraph (g) of the proposed AD (80 FR 32063, June 5, 2015), and create a new paragraph (i) with the repetitive inspection intervals. DAL stated that having the inspection method and the repetitive inspection intervals in one paragraph, as well as a separate paragraph for the initial inspection is cumbersome.

We do not agree with the requested changes. We re-examined the structure of the regulatory text of this AD, and have determined that the specified language as proposed is clear and aligns with the MCAI. Therefore, we have not changed this AD in this regard.

DAL also asked that we add sub-steps to requirements in the proposed AD (80 FR 32063, June 5, 2015), to clarify the inspection requirements specified in Airbus Service Bulletin A320–57–1178, Revision 01, dated May 28, 2014.

We do not agree. Our goal in referring to the Accomplishment Instructions of the service information is to ensure that operators follow the details in the inspection steps shown therein. DAL has the option of creating task cards if it makes accomplishing the sub-steps easier, provided the cards meet the intent of the AD. We have not changed this AD in this regard.

Additionally, DAL asked that Appendix 01 of Airbus Service Bulletin A320–57–1178, Revision 01, dated May 28, 2014, be removed from the service bulletin identification in the NPRM (80 FR 32063, June 5, 2015), because Appendix 01 has Gantt Chart information that should not be highlighted as a regulatory requirement for compliance.

We do not agree. The information in Appendix 01 of Airbus Service Bulletin A320–57–1178, Revision 01, dated May 28, 2014, may be helpful to operators that want to determine the number of work hours necessary to accomplish specific actions. Moreover, Appendix 01 does not contain a requirement for compliance. We have not changed this AD in this regard.

Conclusion

We reviewed the relevant data and determined that air safety and the public interest require adopting this AD as proposed, with minor editorial changes. We have determined that these minor changes:

• Are consistent with the intent that was proposed in the NPRM (80 FR 32063, June 5, 2015) for correcting the unsafe condition; and • Do not add any additional burden upon the public than was already proposed in the NPRM (80 FR 32063, June 5, 2015).

We have also determined that these changes will not increase the economic burden on any operator or increase the scope of this AD.

Related Service Information Under 1
CFR Part 51

Airbus has issued Service Bulletin A320–57–1178, Revision 01, dated May 28, 2014, including Appendix 01, dated May 28, 2014. The service information describes procedures for inspecting the radius of the front spar vertical stringers and the horizontal floor beam on frame 36 for cracking. This service information is reasonably available because the interested parties have access to it through their normal course of business or by the means identified in the

**ADDRESSES** section.
Costs of Compliance

We estimate that this AD affects 17 airplanes of U.S. registry.

We also estimate that it will take about 24 work-hours per product to comply with the basic requirements of this AD. The average labor rate is $85 per work-hour. Based on these figures, we estimate the cost of this AD on U.S. operators to be $34,680, or $2,040 per product.

In addition, we estimate that any necessary follow-on actions will take about 49 work-hours and require parts costing $1,210, for a cost of $5,375 per product. We have no way of determining the number of aircraft that might need this action.
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 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 the 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.
Examining the AD Docket

You may examine the AD docket on the Internet at http:// www.regulations.gov/#!docket Detail;D=FAA-2015-1422; 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 street address for the Docket Operations office (telephone 800–647–5527) is in the **ADDRESSES** section.
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) 98–18–26, Amendment 39–10742 (63 FR 47423, September 8, 1998), and adding the following new AD:

2016–01–11 Airbus: Amendment 39–18370. Docket No. FAA–2015–1422; Directorate Identifier 2014–NM–125–AD.


### 3318 Federal Register / Vol. 81, No. 13 / Thursday, January 21, 2016 / Rules and Regulations

(a) Effective Date

This AD becomes effective February 25,

2016.

(b) Affected ADs

This AD replaces AD 98–18–26, Amendment 39–10742 (63 FR 47423, September 8, 1998).
(c) Applicability

This AD applies to Airbus Model A320– 211, –212, and –231 airplanes, certificated in any category, manufacturer serial numbers (MSN) 0001 through 0155 inclusive.
(d) Subject

Air Transport Association (ATA) of America Code 57, Wings.

(e) Reason

This AD was prompted by cracks found on the front vertical stringer at frame 36. This AD was also prompted by reports that indicate new repetitive inspections having new thresholds and intervals are needed and that additional work is needed to accomplish the inspections on airplanes on which a previous modification has been accomplished. We are issuing this AD to detect and correct fatigue cracking of the front spar vertical stringers on the wings, which could result in the reduced structural integrity of the airframe.
(f) Compliance

Comply with this AD within the compliance times specified, unless already done.
(g) Inspections

Within the applicable compliance times specified in paragraphs (h)(1) through (h)(4) of this AD, do a high frequency eddy current (HFEC) inspection for cracking of the radius of the front spar vertical stringers and the horizontal floor beam on frame 36, and do a rototest inspection for cracking of the fastener holes of the front spar vertical stringers on frame 36, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320–57–1178, Revision 01, dated May 28, 2014, including Appendix 01, dated May 28, 2014. Repeat the inspections thereafter at the compliance times specified in paragraphs (g)(1) and (g)(2) of this AD.

(1) For Configuration 1 airplanes identified in paragraph (h)(1) of this AD: At intervals not to exceed 8,800 flight cycles or 17,700 flight hours, whichever occurs first.

(2) For Configuration 2, 3, and 4 airplanes identified in paragraphs (h)(2) through (h)(4) of this AD: At intervals not to exceed 24,900 flight cycles or 49,800 flight hours, whichever occurs first.
(h) Compliance Times for Initial Inspections Required by Paragraph (g) of This AD

Do the initial inspections required by paragraph (g) of this AD within the applicable compliance times specified in paragraphs (h)(1) through (h)(4) of this AD.

(1) For Configuration 1 airplanes, having MSNs 0001 through MSN 0079 inclusive, on which the modification specified by Airbus Service Bulletin A320–57–1017, dated September 3, 1991; or Airbus Service Bulletin A320–57–1017, Revision 01, dated March 17, 1997, has not been accomplished: Inspect at the later of the times specified by paragraphs (h)(1)(i) through (h)(1)(iii) of this
AD.

(i) Inspect at the later of the times specified by paragraphs (h)(1)(i)(A) and (h)(1)(i)(B) of this AD.

(A) Prior to the accumulation of 24,000 flight cycles or 48,000 flight hours, whichever occurs first since airplane first flight.

(B) Within 60 days after the effective date of this AD.

(ii) Inspect within 8,800 flight cycles or 17,700 flight hours, whichever occurs first, since the last inspection specified in Airbus Service Bulletin A320–57–1016 was accomplished.

(iii) Inspect within 850 flight cycles or 1,700 flight hours, whichever occurs first, after the effective date of this AD, without exceeding 14,000 flight cycles after the last inspection specified in Airbus Service Bulletin A320–57–1016 was accomplished.

(2) For Configuration 2 airplanes, having MSNs 0001 through 0079 inclusive, on which the actions specified by Airbus Service Bulletin A320–57–1016, have not been done prior to accomplishing the actions specified by Airbus Service Bulletin A320– 57–1017, dated September 3, 1991; or Airbus Service Bulletin A320–57–1017, Revision 01, dated March 17, 1997: Inspect at the later of the times specified by paragraphs (h)(2)(i) and (h)(2)(ii) of this AD.

(i) Within 8,800 flight cycles or 17,700 flight hours, whichever occurs first, since the modification specified in Airbus Service Bulletin A320–57–1017, dated September 3, 1991; or Airbus Service Bulletin A320–57– 1017, Revision 01, dated December 6, 1995, was accomplished.

(ii) Within 850 flight cycles or 1,700 flight hours, whichever occurs first, after the effective date of this AD.

(3) For Configuration 3 airplanes, having MSNs 0001 through 0079 inclusive, on which the actions specified by Airbus Service Bulletin A320–57–1016, have been done prior to accomplishing the actions specified by Airbus Service Bulletin A320– 57–1017, dated September 3, 1991; or Airbus Service Bulletin A320–57–1017, Revision 01, dated March 17, 1997: Inspect at the later of the times specified by paragraphs (h)(3)(i) and (h)(3)(ii) of this AD.

(i) Within 24,900 flight cycles or 49,800 flight hours, whichever occurs first, since the modification specified in Airbus Service Bulletin A320–57–1017, dated September 3, 1991; or Airbus Service Bulletin A320–57– 1017, Revision 01, dated March 17, 1997, was accomplished.

(ii) Within 850 flight cycles or 1,700 flight hours, whichever occurs first, after the effective date of this AD.

(4) For Configuration 4 airplanes, having MSNs 0080 through 0155 inclusive: Inspect at the later of the times specified in paragraphs (h)(4)(i) or (h)(4)(ii) of this AD.

(i) Prior to the accumulation of 54,300 flight cycles or 108,600 flight hours, whichever occurs first since airplane first flight.

(ii) Within 60 days after the effective date of this AD. (i) Repair If any crack is detected during any inspection required by paragraph (g) of this AD: Before further flight, repair using a method approved by the Manager, International Branch, ANM–116, Transport Airplane Directorate, FAA; or the European Aviation Safety Agency (EASA); or Airbus’s EASA Design Organization Approval (DOA).
(j) 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: Sanjay Ralhan, Aerospace Engineer, International Branch, ANM–116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057–3356; telephone 425–227–1405; 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) Contacting the Manufacturer: As of the effective date of this AD, for any requirement in this AD to obtain corrective actions from a manufacturer, the action must be accomplished using a method approved by the Manager, International Branch, ANM– 116, Transport Airplane Directorate, FAA; or the EASA; or Airbus’s EASA DOA. If approved by the DOA, the approval must include the DOA-authorized signature.

(k) Related Information

Refer to Mandatory Continuing Airworthiness Information (MCAI) EASA Airworthiness Directive 2014–0069, dated March 19, 2014, for related information. This MCAI may be found in the AD docket on the
Internet at http://www.regulations.gov by searching for and locating Docket No. FAA–

2015–1422.
(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 this AD specifies otherwise.

(3) The following service information was approved for IBR on February 25, 2016.

(i) Airbus Service Bulletin A320–57–1178, Revision 01, dated May 28, 2014, including Appendix 01, dated May 28, 2014.

(ii) Reserved. (4) For service information identified in this AD, contact Airbus, Airworthiness Office—EIAS, 1 Rond Point Maurice


### 3319 Federal Register / Vol. 81, No. 13 / Thursday, January 21, 2016 / Rules and Regulations

Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61 93 44 51; email account.airworth-eas@ airbus.com; Internet http://www.airbus.com

.

(5) You may view this 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.

(6) 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

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Issued in Renton, Washington, on December 31, 2015. Philip Forde, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service.

[FR Doc. 2016–00373 Filed 1–20–16; 8:45 am]

**BILLING CODE 4910–13–P**

**DEPARTMENT OF TRANSPORTATION**

**Federal Aviation Administration**

**14 CFR Part 39**

**[Docket No. FAA–2015–1998; Directorate Identifier 2014–SW–035–AD; Amendment**  **39–18379; AD 2016–01–19]**

**RIN 2120–AA64**

**Airworthiness Directives; MD Helicopters Inc.** 

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

**ACTION :**  Final rule.

**SUMMARY :**  We are adopting a new airworthiness directive (AD) for MD Helicopters Inc. (MDHI) Model 500N and 600N helicopters with certain rotating cone assemblies installed. This AD requires establishing a life limit of 10,000 hours time-in-service (TIS) on these rotating cone assemblies. This AD was prompted by the determination that MDHI created rotating cone assemblies with new dash numbers but incorrectly failed to identify them as life-limited parts. The actions are intended to prevent operation of rotating cone assemblies past their life limits, failure of the rotating cone assemblies, loss of directional control, and subsequent loss of control of the helicopter.

**DATES :**  This AD is effective February 25,

2016.

**ADDRESSES :**  For service information identified in this final rule, contact MD Helicopters, Inc., Attn: Customer Support Division, 4555 E. McDowell Rd., Mail Stop M615, Mesa, AZ 85215– 9734; telephone 1–800–388–3378; fax
480–346–6813; or at http:// www.mdhelicopters.com . You may review a copy of the referenced service information at the FAA, Office of the Regional Counsel, Southwest Region, 10101 Hillwood Pkwy, Room 6N–321, Fort Worth, TX 76177.
Examining the AD Docket

You may examine the AD docket on the Internet at http:// www.regulations.gov by searching for and locating Docket No. FAA–2015– 1998; 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 (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 :**  Galib Abumeri, Aerospace Engineer, Los Angeles Aircraft Certification Office, Transport Airplane Directorate, FAA, 3960 Paramount Blvd., Lakewood, California 90712, telephone 562–627– 5324; email Galib.Abumeri@faa.gov

.
**SUPPLEMENTARY INFORMATION :** 

Discussion

On June 9, 2015, at 80 FR 32508, 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 MDHI Model 500N helicopters with a rotating cone assembly part number (P/ N) 500N3740–81 installed, and Model 600N helicopters with a rotating cone assembly P/N 500N3740–71 installed. The NPRM proposed to require establishing a life limit of 10,000 hours TIS on these rotating cone assemblies. Although these parts have a life limit of 10,000 hours TIS, they were incorrectly omitted from the Airworthiness Limitation Section of the Rotorcraft Maintenance Manual. Some of the affected parts were sold as spares, while others were installed on new helicopters in production. The proposed requirements were intended to prevent operation of rotating cone assemblies past their life limits, failure of the rotating cone assemblies, loss of directional control, and subsequent loss of control of the helicopter.

Since the NPRM was issued, the FAA Southwest Regional Office has relocated. This AD includes the current physical address of the FAA Southwest Regional Office. Comments
We gave the public the opportunity to participate in developing this AD, but we received no comments on the NPRM (80 FR 32508, June 9, 2015).

FAA’s Determination

We have reviewed the relevant information and determined that an unsafe condition exists and is likely to exist or develop on other products of these same type designs and that air safety and the public interest require adopting the AD requirements as proposed.

Related Service Information

MDHI issued Service Bulletin SB500N–046 and SB600N–054 (SB) as a single bulletin on July 9, 2012. The SB calls for a one-time inspection within 100 flight hours to determine the rotating cone assembly’s part number on MDHI Model 500N and 600N helicopters. The SB then states the need to correct the component record for certain rotating cone assemblies.

The SB also specifies determining the rotating cone assembly’s total service time since new and recording this on the component record. MDHI reports that failure to comply with the SB may result in an aircraft exceeding the life limit of the rotating cone assembly and that this could lead to component failure and loss of directional control of the helicopter.

Differences Between This AD and the Service Information

The SB calls for inspecting the rotating cone assembly to determine its P/N. We make no requirement about how to determine the P/N. The compliance time for the SB is within 100 flight hours, while this AD requires compliance within 1 year or by the next annual inspection, whichever comes later.
Costs of Compliance

We estimate that this AD affects 8 helicopters of U.S. Registry and that labor costs average $85 a work hour. We estimate that creating a component history card and revising the appropriate records takes 1 work-hour. No parts are needed for a total cost of $85 per helicopter and $680 for the U.S. 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