### 78699 Federal Register / Vol. 78, No. 249 / Friday, December 27, 2013 / Rules and Regulations

**DEPARTMENT OF TRANSPORTATION**

**Federal Aviation Administration**

**14 CFR Part 39**

**[Docket No. FAA–2013–0603; Directorate Identifier 2009–SW–079–AD; Amendment**  **39–17706; AD 2013–25–10]**

**RIN 2120–AA64**

**Airworthiness Directives; Bell Helicopter Textron Canada Limited**  **Helicopters**

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

**ACTION :**  Final rule.

**SUMMARY :**  We are adopting a new airworthiness directive (AD) for certain serial-numbered Bell Helicopter Textron Canada Limited (BHTC) Model 206L, 206L–1, 206L–3, and 206L–4 helicopters with a certain tailboom upper left attachment fitting (fitting). This AD requires inspecting the fitting for a crack and other conditions. This AD was prompted by the manufacturer revisingand extending the 100 hour time-inservice (TIS) inspection requirements for the fitting. The actions of this AD are intended to detect a crack, loose rivet, corrosion, or any other damage, which could lead to loss of the tailboom and subsequent loss of control of the helicopter.

**DATES :**  This AD is effective January 31,

2014.

The Director of the Federal Register approved the incorporation by reference of a certain document listed in this AD as of January 31, 2014.

**ADDRESSES :**  For service information identified in this AD, contact Bell Helicopter Textron Canada Limited, 12,800 Rue de l’Avenir, Mirabel, Quebec J7J1R4, telephone (450) 437–2862 or (800) 363–8023, fax (450) 433–0272, or

at http://www.bellcustomer.com/files/. 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 :**  Sharon Miles, Aerospace Engineer, FAA, Regulations and Policy Group, 2601 Meacham Blvd., Fort Worth, Texas 76137; telephone: (817) 222–5110; email: sharon.y.miles@faa.gov.

**SUPPLEMENTARY INFORMATION :** 

Discussion

On July 12, 2013, at 78 FR 41886, the Federal Register published our notice of proposed rulemaking (NPRM), which proposed to amend 14 CFR part 39 to add an AD that would apply to BHTC Model 206L, 206L–1, 206L–3, and 206L–4 helicopters with an upper left attachment fitting part number 206– 032–409–001 installed. The NPRM proposed to require within 100 hours TIS and thereafter at intervals not exceeding 110 hours TIS, inspecting the upper left tailboom attachment fitting for a crack, corrosion, damage, or a loose rivet. If there is a crack or corrosion or damage beyond acceptable limits, the NPRM proposed to require replacing the upper left tailboom attachment fitting. If there is corrosion or damage within acceptable limits, the NPRM proposed to require repairing the fitting. If there is a loose rivet, the NPRM proposed to require replacing the loose rivet. The proposed requirements were intended to detect a crack, loose rivet, corrosion, or any other damage, which could lead to loss of the tailboom and subsequent loss of control of the helicopter.

The NPRM was prompted by AD No. CF–2009–41, dated November 16, 2009, issued by Transport Canada Civil Aviation (TCCA), which is the aviation authority for Canada. TCCA issued AD No. CF–2009–41 to correct an unsafe condition for certain 206L series helicopters, specifically: Model 206L, serial number (S/N) 45004 through 45153, and 46601 through 46617; Model 206L–1, S/N 45154 through 45790; Model 206L–3, S/N 51001 through 51612; and Model 206L–4, all S/Ns. TCCA advises that AD No. CF–2009–41 was prompted by a new airworthiness limitation for the fitting that requires an inspection of fitting part number 203– 032–409–001 at each 100-hour or annual inspection. The TCCA AD requires inspecting the fitting, and replacing or repairing it if necessary, in accordance with the Accomplishment Instructions of BHTC Alert Service Bulletin (ASB) 206L–09–158, Revision A, dated August 31, 2009 (ASB 206L– 09–158 Revision A). TCCA further states that incorporating this inspection into the applicable maintenance manual revision constitutes terminating action to TCCA AD No. CF–2009–41. The actions in TCCA AD No. CF–2009–41 are intended to detect a crack in a tailboom attachment fitting, which could result in loss of the tailboom and subsequent loss of control of the helicopter.

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 41886, July 12, 2013).

FAA’s Determination

These helicopters have been approved by the aviation authority of Canada and are approved for operation in the United States. Pursuant to our bilateral agreement with Canada, TCCA, its technical representative, has notified us of the unsafe condition described in the TCCA AD. We are issuing this AD because we evaluated all information provided by TCCA 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 TCCA AD

The TCCA AD requires a recurring inspection every 100 hours, while this AD requires the inspection at intervals not to exceed 110 hours to align with the Bell ASB.

Related Service Information

We reviewed ASB 206L–09–158, Revision A for certain serial-numbered Model 206L, L–1, L–3, and L–4 helicopters with certain tailboom assemblies installed. The ASB requires an inspection of the fitting for a crack, loose rivets, corrosion, and damage at each 100-hour or annual inspection. If there is a crack, the ASB specifies replacing the fitting with an airworthy fitting. If there is a loose rivet, the ASB specifies replacing the rivet with an airworthy rivet. If the fitting has corrosion or mechanical damage, the ASB specifies determining if the corrosion or mechanical damage is within acceptable limits. If the corrosion or mechanical damage is within acceptable limits, the ASB specifies repairing the damage in accordance with the instructions contained in the ASB. If the damage is not within acceptable limits, the ASB specifies replacing the fitting with an airworthy


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fitting. TCCA classified this ASB as mandatory and issued AD No. CF– 2009–41 to ensure the continued airworthiness of these helicopters.

Since that time, BHTC has issued ASB 206L–09–158, Revision B, dated June 1, 2011, for all Model 206L series helicopters. Revision B of the ASB changes the recurring inspection interval from every 100 flight hours to every 110 flight-hours.
Costs of Compliance

We estimate that this AD affects 783 helicopters of U.S. Registry. We estimate that operators may incur the following costs in order to comply with this AD.At an average labor rate of $85 per workhour, inspecting the fitting requires about 1 work-hour, for a cost per helicopter of $85 and a total cost to U.S. operators of $66,555 per inspection cycle.

We estimate the following costs to do any necessary repairs or replacements that would be required based on the results of the proposed inspection. We have no way of determining the number of aircraft that might need these repairs or replacements. Repairing a damaged fitting requires about 8 work-hours and required parts cost about $10, for a cost per helicopter of $690. Replacing a fitting which is damaged beyond the allowable repair limits requires about 8 work-hours and required parts cost about $793, for a cost per helicopter of $1,473. Replacing a loose rivet requires about 1 work-hour, and required parts cost about $1, for a cost per helicopter of $86.
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):
2013–25–10 Bell Helicopter Textron Canada (BHTC): Amendment 39–17706; Docket No. FAA–2013–0603; Directorate Identifier 2009–SW–079–AD.
(a) Applicability

This AD applies to BHTC Model 206L, 206L–1, 206L–3, and 206L–4 helicopters with an upper left attachment fitting part number 206–032–409–001 installed, certificated in any category.

(b) Unsafe Condition

This AD defines the unsafe condition as a crack in a tailboom attachment fitting, which could result in loss of the tailboom and subsequent loss of control of the helicopter. (c) Effective Date This AD becomes effective January 31,
2014. (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) At the next 100-hour inspection, and thereafter at intervals not to exceed 110 hours time-in-service, inspect each tailboom upper left attachment fitting (fitting) for a crack, a loose rivet, corrosion, or damage as depicted in Figure 2 of BellAlert Service Bulletin 206L–09–158, Revision B, dated June 1, 2011 (ASB 206L–09–158).

(2) If there is a crack, corrosion, or damage beyond the acceptable limits of Figure 2 of ASB 206L–09–158, before further flight, replace the fitting with an airworthy fitting.

(3) If there is corrosion or damage within the acceptable limits of Figure 2 of ASB 206L–09–158, before further flight, repair the fitting as described in the Accomplishment Instructions, Part I, paragraphs 5.b.(1) through 5.b.(6), of ASB 206L–09–158.

(4) If there is a loose rivet, before further flight, replace the loose rivet with an airworthy rivet.
(f) Alternative Methods of Compliance (AMOCs)

(1) The Manager, Safety Management Group, FAA, may approve AMOCs for this AD. Send your proposal to: Sharon Miles, Aerospace Engineer, FAA, Regulations and Policy Group, 2601 Meacham Blvd., Fort Worth, Texas 76137; telephone: (817) 222– 5122; fax: (817) 222–5961; email: sharon.y.miles@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 Transport Canada Civil Aviation (TCCA) AD No. CF–2009–41, dated November 16, 2009. You may view the TCCA AD at http:// www.regulations.gov in Docket No. FAA–

2013–0603. (h) Subject

Joint Aircraft Service Component (JASC) Code: 5302: Rotorcraft Tailboom.
(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.

(i) Bell Alert Service Bulletin 206L–09– 158, Revision B, dated June 1, 2011.

(ii) Reserved.


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(3) For Bell service information identified in this AD, contact Bell Helicopter Textron Canada Limited, 12,800 Rue de l’Avenir, Mirabel, Quebec J7J1R4, telephone (450) 437–2862 or (800) 363–8023, fax (450) 433– 0272, or at http://www.bellcustomer.com/ files/.

(4) You may view this service information at 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.

(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 Fort Worth, Texas, on December 5, 2013. Kim Smith, Directorate Manager, Rotorcraft Directorate, Aircraft Certification Service.

[FR Doc. 2013–30186 Filed 12–26–13; 8:45 am]

**BILLING CODE 4910–13–P**

**DEPARTMENT OF TRANSPORTATION**

**Federal Aviation Administration**

**14 CFR Part 39**

**[Docket No. FAA–2013–0421; Directorate Identifier 2013–NM–003–AD; Amendment**  **39–17701; AD 2013–25–05]**

**RIN 2120–AA64**

**Airworthiness Directives; The Boeing Company Airplanes** 

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

**ACTION :**  Final rule.

**SUMMARY :**  We are adopting a new airworthiness directive (AD) for certain The Boeing Company Model 737–300, –400, and –500 series airplanes. This AD was prompted by fuel system reviews conducted by the manufacturer. This AD requires, depending on airplane configuration, replacing fuel pump power control relays with new relays having a ground fault interrupter (GFI) feature, installing ground studs and a bonding jumper, doing certain bonding resistance measurements, and changing the GFI relay position. This AD also requires revising the maintenance program to incorporate certain airworthiness limitations. We are issuing this AD to prevent damage to the fuel pumps caused by electrical arcing that could introduce an ignition source in the fuel tank, which, in combination with flammable fuel vapors, could result in a fuel tank explosion and consequent loss of the airplane.

**DATES :**  This AD is effective January 31,

2014.

The Director of the Federal Register approved the incorporation by reference of certain publications listed in this AD as of January 31, 2014.

**ADDRESSES :**  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. 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.
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 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 20590.

**FOR FURTHER INFORMATION CONTACT :**  Georgios Roussos, Aerospace Engineer, Systems and Equipment Branch, ANM– 130S, FAA, Seattle Aircraft Certification Office, 1601 Lind Avenue SW., Renton, WA 98057–3356; phone: 425–917–6482; fax: 425–917–6590; email: georgios.roussos@faa.gov.

**SUPPLEMENTARY INFORMATION :** 

Discussion

We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 to include an AD that would apply to the specified products. The NPRM published in the Federal Register on May 16, 2013 (78 FR 28764). The NPRM proposed to require, depending on airplane configuration, replacing fuel pump power control relays with new relays having a ground fault interrupter (GFI) feature, installing ground studs and a bonding jumper, doing certain bonding resistance measurements, and changing the GFI relay position. The NPRM also proposed to require revising the maintenance program to incorporate certain airworthiness limitations.

Comments

We gave the public the opportunity to participate in developing this AD. The following presents the comments received on the proposal (78 FR 28764, May 16, 2013) and the FAA’s response to each comment.
Support for the NPRM

Boeing concurred with the content of the proposed rule.
Request To Include Certain Instructions and Delete Certain Step

All Nippon Airways (ANA) requested that we include instructions for the removal and installation of certain relay sockets, and for removal of paint on the mounting panel under Step 5 of Figure 5 of Boeing Alert Service Bulletin 737– 28A1212, Revision 2, dated October 18, 2012. ANA stated that without removal of the paint on the mounting panel, the required bonding resistance measurements cannot be obtained. In addition, ANA requested that we delete step 6 of Figure 5 of Boeing Alert Service Bulletin 737–28A1212, Revision 2, dated October 18, 2012, which describes removal of paint around the relay cutout. ANA stated that paint removal around the relay cutout is not needed since the relay sockets are mounted to the cutout area of the panel and the relays are a spacer-mounted type.

We disagree with providing additional instructions that would expand the scope of this final rule, requiring additional notice and comment. We find that delaying this action would be inappropriate in light of the urgency of the identified unsafe condition. Operators should note that a general AMOC, which was requested by Boeing on behalf of all operators, has been issued for AD 2011–12–09, Amendment 39–16716 (76 FR 33988, June 10, 2011). The AMOC provides essentially the same relief as that requested by the commenter. Once this final rule is effective, we may issue a similar AMOC. Any person may request approval of an alternative method of compliance (AMOC) under the provisions of paragraph (l) of this AD for procedures that help them meet the bonding resistance requirements. We have not changed this final rule in this regard.

Conclusion

We reviewed the relevant data, considered the comments received, and determined that air safety and the public interest require adopting this AD