## 13528 Federal Register / Vol. 79, No. 47 / Tuesday, March 11, 2014 / Rules and Regulations

Authority: 49 U.S.C. 106(g), 40113, 44701.

**§ 39.13 [Amended]**

■ 

### 2. The FAA amends § 39.13 by removing Airworthiness Directive (AD) 2010–11–51, Amendment 39–16396 (75 FR 50874, August 18, 2010), and adding the following new AD:
2014–05–07 Airbus Helicopters (Type Certificate Previously Held by Eurocopter France): Amendment 39– 17780; FAA–2013–0477; Directorate Identifier 2011–SW–015–AD.
(a) Applicability

This AD applies to Model AS350B, BA, B1, B2, C, D, and D1 helicopters and Model AS355E, F, F1, F2, and N helicopters, with a tail gearbox (TGB) control lever, part number (P/N) 350A33–1058–00, P/N 350A33–1058–01, P/N 350A33–1058–02, or P/N 350A33–1058–03, both with and without an ‘‘X’’ marked near the P/N, installed, certificated in any category.
(b) Unsafe Condition

This AD defines the unsafe condition as a crack in the TGB control lever. This condition could result in failure of the TGB control lever, loss of tail rotor control, and subsequent loss of control of the helicopter.
(c) Affected ADs

This AD supersedes AD 2010–11–51, Amendment 39–16396 (75 FR 50874, August 18, 2010).
(d) Effective Date

This AD becomes effective April 15, 2014.
(e) 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.
(f) Required Actions

(1) For helicopters with a lever not marked with an ‘‘X’’ near the P/N, within 10 hours time-in-service (TIS), and thereafter at intervals not to exceed 10 hours TIS, using a mirror and appropriate light source, visually inspect the TGB control lever for a crack as shown in area ‘‘A’’ of Figure 2 of Eurocopter Emergency Alert Service Bulletin No. 05.00.62, Revision 2, dated March 1, 2011 (EASB No. 05.00.62), for Model AS350 helicopters, and Eurocopter Emergency Alert Service Bulletin No. 05.00.57, Revision 2, dated March 1, 2011 (EASB No. 05.00.57), for Model AS355 helicopters. If there is a crack, before further flight, replace each cracked TGB control lever with a TGB control lever with a P/N not listed in paragraph (a) of this AD.

(2) For Model AS355N helicopters, within 110 hours TIS, or if the helicopter has reached 100 or more hours TIS, within the next 10 hours TIS, and thereafter at intervals not to exceed 110 hours TIS, using a mirror and appropriate light source, inspect each TGB control lever for a crack as shown in area ‘‘C’’ of Figure 8 of EASB No. 05.00.62 or EASB No. 05.00.57, as applicable to your model helicopter. (3) Within 660 hours TIS, replace each TGB control lever with a reworked TGB control lever marked with an ‘‘X’’ near the P/ N or with a TGB control lever with a P/N not listed in paragraph (a) of this AD.

(4) For all model helicopters except Model AS355N, within 660 hours TIS, or if the helicopter has reached 605 or more hours TIS within the next 55 hours TIS, and thereafter at intervals not to exceed 660 hours TIS, using a mirror and appropriate light source, inspect each TGB control lever for a crack as shown in area ‘‘C’’ of Figure 8 of EASB No. 05.00.62 or EASB No. 05.00.57, as applicable to your model helicopter.

(5) If there is a crack, before further flight, replace each cracked TGB control lever with a TGB control lever with a P/N not listed in paragraph (a) of this AD.
(g) Alternative Methods of Compliance (AMOCs)

(1) The Manager, Safety Management Group, FAA, may approve AMOCs for this AD. Send your proposal to: Robert Grant, Aviation Safety Engineer, FAA, Rotorcraft Directorate, Safety Management Group, 2601 Meacham Blvd., Fort Worth, TX 76137, telephone (817) 222–5110, email robert.grant@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) Related Information

The subject of this AD is addressed in European Aviation Safety Agency (EASA) Emergency AD No. 2011–0038–E, dated March 4, 2011, and superseded EASA Emergency AD No. 2010–0082–E, dated April 27, 2010. You may view the EASA AD on the Internet at http://www.regulations.gov in Docket No. FAA–2013–0477.
(i) Subject

Joint Aircraft Service Component (JASC) Code: 6720 Tail Rotor Control 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) Eurocopter Emergency Alert Service Bulletin (EASB), No. 05.00.62,

Revision 2, dated March 1, 2011. (ii) Eurocopter EASB No. 05.00.57, Revision 2, dated March 1, 2011.

Note 1 to paragraph (j)(2): Eurocopter EASB No. 05.00.62, Revision 2, dated March 1, 2011, and Eurocopter EASB No. 05.00.57,Revision 2, dated March 1, 2011, are copublished as one document along with Eurocopter EASB No. 05.00.38, Revision 2, dated March 1, 2011, and Eurocopter EASB No. 05.00.35, Revision 2, dated March 1, 2011, which are not incorporated by reference in this AD.

(3) For Eurocopter service information identified in this AD, contact Airbus Helicopters, Inc., 2701 N. Forum Drive, Grand Prairie, TX 75052; telephone (972) 641–0000 or (800) 232–0323; fax (972) 641– 3775; or at http:// www.airbushelicopters.com/techpub.

(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 February 26, 2014. Bruce E. Cain, Acting Directorate Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. 2014–04729 Filed 3–10–14; 8:45 am]

**BILLING CODE 4910–13–P**



### DEPARTMENT OF TRANSPORTATION

**Federal Aviation Administration**

**14 CFR Part 39**

**[Docket No. FAA–2013–0798; Directorate Identifier 2013–NM–087–AD; Amendment**  **39–17796; AD 2014–05–23]**

**RIN 2120–AA64**



### Airworthiness Directives; Bombardier, **Inc. Airplanes**

**AGENCY** 

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

**ACTION** 

### : Final rule.

**SUMMARY** 

### : We are adopting a new airworthiness directive (AD) for certain Bombardier, Inc. Model BD–100–1A10 (Challenger 300) airplanes. This AD was prompted by multiple reports of erratic electrical status indications on the push button annunciators and the engine instrument and crew alerting system. Certain of those reported incidents resulted in the airplane experiencing a momentary loss of electrical power and loss of flight displays. This AD requires modification of the direct current power centers. We are issuing this AD to prevent loss of electrical power, which could result in the loss of flight displays and reduced controllability of the airplane.

**DATES** 

### : This AD becomes effective April 15, 2014.


## 13529 Federal Register / Vol. 79, No. 47 / Tuesday, March 11, 2014 / Rules and Regulations

The Director of the Federal Register approved the incorporation by reference of a certain publication listed in this AD as of April 15, 2014.

**ADDRESSES** 

### : You may examine the AD docket on the Internet at http:// www.regulations.gov/ #!docketDetail;D=FAA-2013-0798; 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 Bombardier, Inc., 400 Co

ˆ te-Vertu Road West, Dorval, Que  ́bec H4S 1Y9, Canada; telephone 514–855– 5000; fax 514–855–7401; email thd.crj@ aero.bombardier.com; Internet http:// www.bombardier.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.

**FOR FURTHER INFORMATION CONTACT**

### : Assata Dessaline, Aerospace Engineer, Systems and Flight Test Branch, ANE– 172, FAA, New York Aircraft Certification Office, 1600 Stewart Avenue, Suite 410, Westbury, NY 11590; telephone (516) 228–7301; fax (516) 794–5531.

**SUPPLEMENTARY INFORMATION** 

### :

Discussion

We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 by adding an AD that would apply to certain Bombardier, Inc. Model BD–100–1A10 (Challenger 300) airplanes. The NPRM published in the Federal Register on September 25, 2013 (78 FR 58965). The NPRM was prompted by multiple reports of erratic electrical status indications on the push button annunciators and the engine instrument and crew alerting system. Certain of those reported incidents resulted in the airplane experiencing a momentary loss of electrical power and loss of flight displays. The NPRM proposed to require modification of the direct current power centers. We are issuing this AD to prevent loss of electrical power, which could result in the loss of flight displays and reduced controllability of the airplane.

Transport Canada Civil Aviation (TCCA), which is the aviation authority for Canada, has issued Canadian Airworthiness Directive CF–2013–05, dated February 22, 2013 (referred to after this as the Mandatory Continuing Airworthiness Information, or ‘‘the MCAI’’), to correct an unsafe condition for the specified products. The MCAI
states:

There have been multiple in-service reports of erratic electrical status indications on the Push Button Annunciators (PBA) and the Engine Instrument & Crew Alerting System (EICAS) while on-ground and during flight. Three of those reported incidents resulted in the aeroplane experiencing momentary loss of electrical power and loss of flight displays.

The investigation revealed that improper insertion of a Printed Circuit Board (PCB) in a Direct Current Power Center (DCPC) may lead to erroneous electrical status indications on the PBAs and EICAS. The erroneous indications could mislead the pilots into turning off active generators and leading to partial or complete loss of electrical power. Loss of electrical power could result in the loss of flight displays and reduced controllability of the aeroplane.

Further investigation determined that the design of the existing DCPC covers does not ensure that the PCBs will remain inserted into the motherboard of the DCPC.

This [TCCA] AD mandates the modification of each DCPC to ensure that properly closed covers will retain the PCBs within the motherboards.



### You may examine the MCAI in the AD docket on the Internet at http:// www.regulations.gov/ #!documentDetail;D=FAA-2013-0798-
0001.

Comments

We gave the public the opportunity to participate in developing this AD. We received no comments on the NPRM (78 FR 58965, September 25, 2013) or on the determination of the cost to the public.

Conclusion

We reviewed the relevant data and determined that air safety and the public interest require adopting this 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 58965, September 25, 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 58965, September 25, 2013). Costs of Compliance

We estimate that this AD affects 92 airplanes of U.S. registry.

We also estimate that it will take about 7 work-hours per product to comply with the basic requirements of this AD. The average labor rate is $85 per work-hour. Required parts will cost about $1,568 per product. Based on these figures, we estimate the cost of this AD on U.S. operators to be $198,996, or $2,163 per product. According to the manufacturer, some of the costs of this AD may be covered under warranty, thereby reducing the cost impact on affected individuals. We do not control warranty coverage for affected individuals. As a result, we have included all costs in our cost estimate. 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/ #!docketDetail;D=FAA-2013-0798; 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


## 13530 Federal Register / Vol. 79, No. 47 / Tuesday, March 11, 2014 / Rules and Regulations

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 adding the following new AD:
2014–05–23 Bombardier, Inc.: Amendment 39–17796. Docket No. FAA–2013–0798; Directorate Identifier 2013–NM–087–AD.
(a) Effective Date

This airworthiness directive (AD) becomes effective April 15, 2014.
(b) Affected ADs

None. (c) Applicability

This AD applies to Bombardier, Inc. Model BD–100–1A10 (Challenger 300) airplanes, certificated in any category, serial numbers 20003 and subsequent.
(d) Subject

Air Transport Association (ATA) of America Code 24, Electrical power.
(e) Reason

This AD was prompted by multiple reports of erratic electrical status indications on the push button annunciators and the engine instrument and crew alerting system. Certain of those reported incidents resulted in the airplane experiencing a momentary loss of electrical power and loss of flight displays. We are issuing this AD to prevent loss of electrical power, which could result in the loss of flight displays and reduced controllability of the airplane.
(f) Compliance

You are responsible for having the actions required by this AD performed within the compliance times specified, unless the actions have already been done.
(g) Direct Current Power Centers (DCPC) Modification

For airplanes having serial numbers 20003 through 20405 inclusive: Within 800 flight hours after the effective date of this AD or within 24 months after the effective date of this AD, whichever occurs first, modify the left-hand DCPC, right-hand DCPC, and auxiliary DCPC, in accordance with the Accomplishment Instructions of Bombardier Service Bulletin 100–24–23, dated November 26, 2012.
(h) Parts Installation Limitation

As of the effective date of this AD, no person may install a DCPC having a part number specified in paragraphs (h)(1) through (h)(9) of this AD on any airplane, unless the DCPC serial number has a suffix ‘‘R’’ beside the serial number. (1) 970GC02Y04. (2) 970GC02Y05. (3) 970GC02Y06. (4) 975GC02Y04. (5) 975GC02Y05. (6) 975GC02Y06. (7) 320GC03Y04. (8) 320GC03Y05. (9) 320GC03Y06.
(i) Other FAA AD Provisions

The following provisions also apply to this AD:

(1) Alternative Methods of Compliance (AMOCs): The Manager, New York Aircraft Certification Office (ACO), ANE–170, 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 ACO, send it to ATTN: Program Manager, Continuing Operational Safety, FAA, New York ACO, 1600 Stewart Avenue, Suite 410, Westbury, NY 11590; telephone 516–228–7300; fax 516–794–5531. Before using any approved AMOC, notify your appropriate principal inspector, or lacking a principal inspector, the manager of the local flight standards district office/ certificate holding district office. The AMOC approval letter must specifically reference this AD.

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

Refer to Mandatory Continuing Airworthiness Information (MCAI) Canadian Airworthiness Directive CF–2013–05, dated February 22, 2013, for related information. This MCAI may be found in the AD docket on the Internet at http:// www.regulations.gov/ #!documentDetail;D=FAA-2013-0798-0001.
(k) Material Incorporated by Reference

(1) The Director of the Federal Register approved the incorporation by reference (IBR) of the service information listed in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51.

(2) You must use this service information as applicable to do the actions required by this AD, unless this AD specifies otherwise. (i) Bombardier Service Bulletin 100–24–23, dated November 26, 2012.

(ii) Reserved. (3) For service information identified in this AD, contact Bombardier, Inc., 400 Co ˆ teVertu Road West, Dorval, Que  ́bec H4S 1Y9, Canada; telephone 514–855–5000; fax 514– 855–7401; email thd.crj@ aero.bombardier.com; Internet http:// www.bombardier.com

.

(4) 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.

(5) You may view this service information that is incorporated by reference at the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, call 202–741–6030, or go to: http://www.archives.gov/federal-register/cfr/ibrlocations.html.

Issued in Renton, Washington, on February 26, 2014. Jeffrey E. Duven, Manager, Transport Airplane Directorate, Aircraft Certification Service.
[FR Doc. 2014–04822 Filed 3–10–14; 8:45 am]

**BILLING CODE 4910–13–P**



### DEPARTMENT OF TRANSPORTATION

**Federal Aviation Administration**

**14 CFR Part 39**

**[Docket No. FAA–2013–0977; Directorate Identifier 2013–NM–190–AD; Amendment**  **39–17795; AD 2014–05–22]**

**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 717–200 airplanes. This AD was prompted by multiple reports of cracking in the overwing frames. This AD requires repetitive inspections for cracking in the overwing frames, and corrective actions if necessary. We are issuing this AD to detect and correct such cracking, which could result in a severed frame and might increase the loading of adjacent frames, resulting in damage to the adjacent structure and consequent loss of structural integrity of the airplane.

**DATES** 

### : This AD is effective April 15,
2014.

The Director of the Federal Register approved the incorporation by reference of a certain publication listed in this AD as of April 15, 2014.