### 38546 Federal Register / Vol. 78, No. 124 / Thursday, June 27, 2013 / Rules and Regulations

to assure the product is airworthy before it is returned to service.

(h) Related Information

Refer to MCAI European Aviation Safety Agency (EASA) AD No.: 2012–0270, dated December 20, 2012, for related information, which can be found in the AD docket on the Internet at http://www.regulations.gov.
(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) Britten-Norman Service Bulletin Number SB 332, Issue 1, dated December 6,
2012.

(ii) Reserved. (3) For B–N Group Ltd. service information identified in this AD, contact Britten-Norman Aircraft Ltd, Commodore House, Mountbatten Business Centre, Millbrook Road East, Southampton SO15 1HY, United Kingdom; telephone: +44 01983 872511; fax: +44 01983 873246; email: info@bnaircraft.com; Internet: www.brittennorman.com.

(4) You may view this service information at FAA, Small Airplane Directorate, 901 Locust, Kansas City, Missouri 64106. For information on the availability of this material at the FAA, call (816) 329–4148.

(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/ibr-locations.html.

Issued in Kansas City, Missouri, on June 18, 2013. James E. Jackson, Acting Manager, Small Airplane Directorate, Aircraft Certification Service.
[FR Doc. 2013–14979 Filed 6–26–13; 8:45 am]

**BILLING CODE 4910–13–P**

**DEPARTMENT OF TRANSPORTATION**

**Federal Aviation Administration**

**14 CFR Part 39**

**[Docket No. FAA–2013–0019; Directorate Identifier 2010–SW–051–AD; Amendment**  **39–17485; AD 2013–12–07]**

**RIN 2120–AA64**

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

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

**ACTION :**  Final rule.

**SUMMARY :**  We are adopting a new airworthiness directive (AD) for Bell Helicopter Textron Canada (BHTC) Model 407 helicopters with certain tailboom assemblies installed. This AD requires, at specified intervals, inspecting the tailboom assembly for a crack, loose rivet, or other damage. This AD was prompted by a stress analysis of the tailboom skin that revealed that high-stress-concentration areas are susceptible to skin cracking. This condition, if not detected, could result in a crack in the tailboom assembly, failure of the tailboom, and subsequent loss of control of the helicopter.

**DATES :**  This AD is effective August 1,
2013.

The Director of the Federal Register approved the incorporation by reference of a certain document listed in this AD as of August 1, 2013.

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

**FOR FURTHER INFORMATION CONTACT :**  Sharon Miles, Aerospace Engineer, FAA, Regulations and Policy Group, 2601 Meacham Blvd., Fort Worth, Texas 76137; telephone (817) 222–5110; fax (817) 222–5110; email sharon.y.miles@faa.gov.

**SUPPLEMENTARY INFORMATION :** 

Discussion

Transport Canada, which is the aviation authority for Canada, has issued AD CF–2009–07, dated March 6, 2009 (AD CF–2009–07), to correct an unsafe condition for the BHTC Model 407 helicopters with a tailboom assembly, part number (P/N) 407–030– 801–201, –203, or –205. Transport Canada states that a stress analysis of the chemically milled tailboom skin ‘‘revealed a possibility of skin cracking due to high stress concentration areas.’’ Transport Canada advises that this condition, if not detected, could result in ‘‘serious damage to the tailboom.’’

On February 1, 2013, at 78 FR 7308, 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 BHTC Model 407 helicopters, with tailboom assembly part number (P/N) 407–030–801–201, 407–030–801–203, or 407–030–801–205. The NPRM proposed to require, at specified intervals, inspecting the tailboom assembly for a crack, loose rivet, or other damage. The proposed requirements were intended to prevent a crack in the tailboom assembly, failure 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 received no comments on the NPRM (78 FR 7308, February 1, 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, Transport Canada, 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 Canada and determined that an 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 Transport Canada AD

The Transport Canada AD states to perform the inspections of the tailboom ‘‘in accordance with inspection procedures as per applicable part’’ of the ASB. This proposed AD references only specific sections of the ASB for accomplishing the requirements.

Related Service Information

BHTC has issued Alert Service Bulletin No. 407–08–84, dated August 18, 2008 (ASB), which specifies a new inspection schedule for the tailboom assemblies. BHTC states it has not received any field reports indicating cracked skin in service on the tailboom assemblies. However, in the interest of


### 38547 Federal Register / Vol. 78, No. 124 / Thursday, June 27, 2013 / Rules and Regulations

safety, BHTC states it has elected to introduce a new inspection schedule for the tailboom assemblies. The ASB specifies the new inspection schedule. Transport Canada classified this ASB as mandatory and issued AD CF–2009–07 to ensure the continued airworthiness of these helicopters. Costs of Compliance

We estimate that this AD will affect 551 helicopters of U.S. registry, and estimate the cost of compliance for the first year as follows:

• We assume 1 initial 100-hour TIS inspection and 2 recurring inspections, which will each take about 2.5 hours. At an average labor rate of $85 per hour, this will result in a cost of about $213 per inspection per helicopter or a total annual inspection cost for 3 recurring inspections of about $639 per helicopter.

• We assume 1 initial inspection and thereafter 4 recurring inspections per year for helicopters with a tailboom assembly that has 6,900 or more hours TIS, which will each take 3 hours at the average labor rate of $85 per hour or $255 per helicopter. Multiplying this $255 times the 5 recurring inspections, the total annual cost will be $1,275 per helicopter.

• We assume 1 initial inspection and 12 recurring inspections per year for helicopters with a tailboom assembly that has 8,600 or more hours TIS. If each inspection takes 3.25 hours, at the average labor rate of $85 per hour, each inspection will cost about $276. Multiply $276 times the 13 recurring inspections will result in a total annual inspection cost of $3,588 per helicopter. We expect the cost of pilot checks to be minimal.

• Replacing the tailboom will take 10 work hours at an average labor rate of $85 per hour for a total labor cost of $850 per helicopter. Parts will cost $82,850 for a total cost per helicopter of $83,700. Assuming that 5 helicopters per year will need a replacement tailboom, the fleet replacement cost will total $418,500. 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):
2013–12–07 Bell Helicopter Textron Canada (BHTC): Amendment 39–17485; Docket No. FAA–2013–0019; Directorate Identifier 2010–SW–051–AD.
(a) Applicability

This AD applies to BHTC Model 407 helicopters, with tailboom assembly part number (P/N) 407–030–801–201, 407–030– 801–203, or 407–030–801–205, certificated in any category.
(b) Unsafe Condition

This AD defines the unsafe condition as high-stress-concentration areas in the tailboom skin that are at risk of cracking. This condition could result in a crack in the tailboom assembly, failure of the tailboom, and subsequent loss of helicopter control.

(c) Effective Date

This AD becomes effective August 1, 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 helicopters with a tailboomassembly that has 8,600 or more hours timein-service (TIS):

(i) Comply with either paragraph (e)(1)(i)(A) or (e)(1)(i)(B):

(A) Before the first flight of each day, visually check for a crack in the ‘‘C’’ and ‘‘D’’ areas depicted in Figures 1and 2 to Paragraph (e) of this AD. The actions required by this paragraph may be performed by the owner/ operator (pilot) holding at least a private pilot certificate, and must be entered into the aircraft records showing compliance with this AD in accordance with 14 CFR 43.9 (a)(1)–(4) and 14 CFR § 91.417(a)(2)(v). The record must be maintained as required by 14 CFR 91.417, 121.380, or 135.439; or

**BILLING CODE 4910–13–P**


### 38548 Federal Register / Vol. 78, No. 124 / Thursday, June 27, 2013 / Rules and Regulations


AREAB



## Figure 1 to Paragraph (e)

### 38549 Federal Register / Vol. 78, No. 124 / Thursday, June 27, 2013 / Rules and Regulations

**BILLING CODE 4910–13–C**

(B) Within 25 hours TIS, or 30 days, whichever comes first, and thereafter at intervals not to exceed 50 hours TIS, clean and inspect for a crack around each fastener and just above the edge of the upper stabilizer support in the ‘‘C’’ and ‘‘D’’ areas on the left side of the tailboom assembly, as depicted in Figure 2 to Paragraph (e) of this AD, using a 10X or higher power magnifying glass.

(ii) Comply with the requirements of paragraph (e)(2)(i)(A) or (e)(2)(i)(B), and paragraph (e)(3) of this AD.

(2) For helicopters with a tailboom assembly that has 6,900 or more hours TIS:

(i) Within 25 hours TIS or 30 days, whichever occurs first, clean and inspect the tailboom assembly for a crack in the ‘‘H’’ and ‘‘I’’ areas depicted in Figure 2, Sheet 5, of the BHTC Alert Service Bulletin No. 407–08–84, dated August 18, 2008, (ASB), by using one of the two following methods.

(A) Use a 10X or higher power magnifying glass; thereafter, repeat the 10X or higher power magnifying glass inspection at intervals not to exceed 150 hours TIS; or

(B) Eddy current inspect for a crack in accordance with Appendix A and Table 1, and by referencing Figures 3 through 7 of the ASB; thereafter, repeat the eddy current inspection at intervals not to exceed 500 hours TIS. Use a person qualified to Level II or Level III per the National Aerospace Standard (NAS) 410 or equivalent requirements to perform the eddy current inspection. (ii) Comply with the requirements of paragraph (e)(3) of this AD.

(3) Within 100 hours TIS or at the next tailboom inspection, whichever comes first, and thereafter at intervals not to exceed 300 hours TIS:

(i) Clean and inspect the tailboom assembly for a loose rivet, a crack, or other damage in accordance with Part II, paragraphs 2 and 3, of the ASB; and

(ii) Using a 10X or higher power magnifying glass, inspect the tailboom assembly for a loose rivet or a crack in accordance with Part II, paragraphs 4 through 6, of the ASB.

(4) If the total accumulated hours TIS on the tailboom assembly is unknown, assume the tailboom assembly has 8,600 or more hours TIS and clean and inspect in accordance with paragraph (e)(1) of this AD.

(5) If there is a crack in the tailboom assembly, before further flight, replace it with an airworthy tailboom assembly.
(f) Special Flight Permits

Special flight permits may be issued in accordance with 14 CFR 21.197 and 21.199 to operate the helicopter to a location where the requirements of this AD can be accomplished, provided no passenger is on board and any crack or damage is temporarily repaired using FAA-approved procedures.
(g) 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– 5110; 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.

(h) Additional Information

The subject of this AD is addressed in Transport Canada Civil Aviation (TCCA) AD No. CF–2009–07, dated March 6, 2009. You may view the TCCA AD at http:// www.regulations.gov by searching for and locating it in Docket No. FAA–2013–0019.
(i) Subject

Joint Aircraft Service Component (JASC) Code: 5302, rotorcraft tailboom.
(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) Bell Helicopter Textron Canada Alert Service Bulletin No. 407–08–84, dated


### 38550 Federal Register / Vol. 78, No. 124 / Thursday, June 27, 2013 / Rules and Regulations

August 18, 2008, excluding Figure 2 sheets 1 and 4.

(ii) Reserved. (3) For BHTC 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 June 3,
2013. Kim Smith, Directorate Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. 2013–14857 Filed 6–26–13; 8:45 am]

**BILLING CODE 4910–13–P**

**DEPARTMENT OF TRANSPORTATION**

**Federal Aviation Administration**

**14 CFR Part 39**

**[Docket No. FAA–2013–0205; Directorate Identifier 2012–NM–226–AD; Amendment**  **39–17493; AD 2013–13–05]**

**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 all The Boeing Company Model 747SP series airplanes, and certain The Boeing Company Model 747–100B SUD and 747–300 series airplanes. This AD was prompted by an evaluation by the design approval holder indicating that the fuselage skin just above certain lap splice locations is subject to widespread fatigue damage. This AD requires repetitive inspections for cracking of the fuselage skin above certain lap splice locations, and repair if necessary. We are issuing this AD to detect and correct fatigue cracking of the fuselage skin, which could result in reduced structural integrity of the airplane and sudden loss of cabin pressure.

**DATES :**  This AD is effective August 1,
2013.

The Director of the Federal Register approved the incorporation by reference of a certain publication listed in the AD as of August 1, 2013.

**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 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. 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 (ACO), 1601 Lind Avenue SW., Renton, WA 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 include an AD that would apply to the specified products. That NPRM published in the Federal Register on March 7, 2013 (78 FR 14719). That NPRM proposed to require repetitive inspections for cracking of the fuselage skin above certain lap splice locations, and repair if necessary.

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 14719, March 7, 2013).

Conclusion

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

– except for minor editorial changes. We have determined that these minor changes:

• Are consistent with the intent that was proposed in the NPRM (78 FR 14719, March 7, 2013) for correcting the unsafe condition; and

• Do not add any additional burden upon the public than was already proposed in the NPRM (78 FR 14719, March 7, 2013). Costs of Compliance

We estimate that this AD affects 4 airplanes of U.S. registry.

We estimate the following costs to comply with this AD:



### E STIMATED 

### C OSTS

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

Inspection ............................................ Up to 57 work-hours × $85 per hour = $4,845, per inspection cycle. $0 Up to $4,845, per inspection cycle. Up to $19,380, per inspection cycle.

We have received no definitive data that would enable us to provide coststimates 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,