## 53635 Federal Register / Vol. 78, No. 169 / Friday, August 30, 2013 / Rules and Regulations

(d) Subject

Air Transport Association (ATA) of America Code 26, Fire protection.
(e) Reason

This AD was prompted by reports of advance pneumatic detectors (APDs) for engine fire/overheat detector assemblies failing to reset after activation due to permanent deformation of the detector switch diaphragm after being exposed to high temperatures. We are issuing this AD to prevent a continued engine fire indication in the cockpit after the actual fire has been extinguished, which is misleading and might influence the pilot to conduct a potentially hazardous ‘‘off-airport’’ landing.
(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) Installation

Within 6,000 flight hours or 30 months after the effective date of this AD, whichever occurs first, replace the APDs as specified in paragraphs (g)(1), (g)(2), and (g)(3) of this AD, as applicable.

(1) For airplanes having S/Ns 4001 through 4373 inclusive: For the nacelle of the engine primary zone, remove any APD having part number (P/N) 10–1098 and install a new APD having P/N 10–1098–01, in accordance with the Accomplishment Instructions of Bombardier Service Bulletin 84–26–08, Revision B, dated September 24, 2012.

(2) For airplanes having S/Ns 4001 through 4373 inclusive: For the nacelle of the landing gear primary zone, remove any APD having P/N 10–1097 or 10–1097–01 and install a new APD having P/N 10–1097–02, in accordance with the Accomplishment Instructions of Bombardier Service Bulletin 84–26–09, Revision A, dated May 12, 2011.

(3) For all airplanes: For the propeller engine controller, remove any APD having P/N 10–1096, 10–1096–01, or 10–1096–02 (serial number is all numeric characters), and install a new APD having P/N 10–1096–02 (serial number is three alpha and four numeric characters), in accordance with the Accomplishment Instructions of Bombardier Service Bulletin 84–26–12, Revision B, dated October 12, 2012.

(h) Credit for Previous Actions

(1) This paragraph provides credit for actions required by paragraph (g)(1) of this AD, if those actions were performed before the effective date of this AD using the service information specified in paragraph (h)(1)(i) or (h)(1)(ii) of this AD, which are not incorporated by reference in this AD.

(i) Bombardier Service Bulletin 84–26–08, dated March 11, 2011.

(ii) Bombardier Service Bulletin 84–26–08, Revision A, dated May 12, 2011.

(2) This paragraph provides credit for actions required by paragraph (g)(2) of this AD, if those actions were performed before the effective date of this AD using Bombardier Service Bulletin 84–26–09, dated March 11, 2011, which is not incorporated by reference in this AD. (3) This paragraph provides credit for actions required by paragraph (g)(3) of this AD, if those actions were performed before the effective date of this AD using the service information specified in paragraph (h)(3)(i) or (h)(3)(ii) of this AD, which are not incorporated by reference in this AD.

(i) Bombardier Service Bulletin 84–26–12, dated October 12, 2011.

(ii) Bombardier Service Bulletin 84–26–12, Revision A, dated December 13, 2011.
(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 FAA-approved 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

(1) Refer to Mandatory Continuing Airworthiness Information Canadian Airworthiness Directive CF–2012–07R1, effective December 21, 2012, for related information. This MCAI may be found in the AD docket on the Internet at http:// www.regulations.gov.

(2) Service information identified in this AD that is not incorporated by reference may be obtained at the address specified in paragraphs (k)(3) and (k)(4) of this AD.
(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 84–26–08, Revision B, dated September 24, 2012.

(ii) Bombardier Service Bulletin 84–26–09, Revision A, dated May 12, 2011.

(iii) Bombardier Service Bulletin 84–26–12, Revision B, dated October 12, 2012.

(3) For service information identified in this AD, contact Bombardier, Inc., Q-Series Technical Help Desk, 123 Garratt Boulevard, Toronto, Ontario M3K 1Y5, Canada; telephone 416–375–4000; fax 416–375–4539; email thd.qseries@aero.bombardier.com; Internet http://www.bombardier.com

.

(4) 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.

(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 August 1, 2013. Jeffrey E. Duven, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service.

[FR Doc. 2013–19830 Filed 8–29–13; 8:45 am]

**BILLING CODE 4910–13–P**



### DEPARTMENT OF TRANSPORTATION

**Federal Aviation Administration**

**14 CFR Part 39**

**[Docket No. FAA–2013–0422; Directorate Identifier 2012–NM–097–AD; Amendment**  **39–17567; AD 2013–17–03]**

**RIN 2120–AA64**



### Airworthiness Directives; Airbus **Airplanes**

**AGENCY** 

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

**ACTION** 

### : Final rule.

**SUMMARY** 

### : We are adopting a new airworthiness directive (AD) for certain Airbus Model A330–200 and –300 series airplanes; Model A340–200 and –300 series airplanes; and Model A340–541 and –642 airplanes. This final rule was prompted by reports of wing tip brakes (WTBs) losing their braking function in service due to heavy wear on the brake discs. WTBs are designed to stop and hold the mechanical transmission of slats and flaps in certain failure cases. This final rule requires repetitive operational tests of certain WTB pressure-off-brakes (POBs) for performance on the flap and slat systems, and replacement of any affected WTB with a new or serviceable part if the test fails. This final rule also requires eventual replacement of all affected WTBs with a new part, which terminates the repetitive tests. We are issuing this final rule to prevent loss of the WTB braking function, and consequent inability of the flap or slat system to be stopped and held in


## 53636 Federal Register / Vol. 78, No. 169 / Friday, August 30, 2013 / Rules and Regulations

position during operation, which could result in loss of control of the airplane.

**DATES** 

### : This AD is effective October 4,
2013.

The Director becomes the Federal Register approved the incorporation by reference of a certain publication listed in this final rule as of October 4, 2013.

**ADDRESSES** 

### : You may examine the AD docket on the Internet at http:// www.regulations.gov or in person at the U.S. Department of Transportation, Docket Operations, M–30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE., Washington, DC.

**FOR FURTHER INFORMATION CONTACT** 

### : Vladimir Ulyanov, Aerospace Engineer, International Branch, ANM–116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, Washington 98057–3356; telephone (425) 227–1138; fax (425) 227–1149.

**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 21, 2013 (78 FR 29666). The NPRM proposed to correct an unsafe condition for the specified products. The European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Community, has issued EASA Airworthiness Directive 2012–0082, dated May 15, 2012 (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:

Several wing tip brakes (WTB) have lost their braking function in service. Inspection by the manufacturer of these units revealed that the drive shaft was found free to rotate and the braking discs worn. Investigations are still on-going to determine the exact root

cause.

The WTB is a Pressure-Off-Brake (POB) with a multi-plate friction device operated by a spring pack. In operation, the brakes are released by dual hydraulic pistons controlled by electro-hydraulic solenoid valves, energized by the Slat Flap Control Computers (SFCC). The purpose of the WTBs (4 per aeroplane) is to stop and hold the mechanical transmission in position in some specificfailure cases. In such cases, the SFCCs deenergize their WTB solenoids, which remove the hydraulic pressure and lead to the application of the brakes.

This condition, if not detected and corrected, could, in some specific failure cases, result in loss of control of the aeroplane.

For the reasons described above, EASA issued AD 2010–0267 [( http:// ad.easa.europa.eu/blob/easa

_ ad

_2012

_ 0082.pdf/AD

_ 2010-0267)] to require a onetime Operational Test of the WTB/POB performance on the flap and slat systems to detect any dormant failure and, depending on findings, applicable corrective actions. This AD also required the reporting of findings, including none, to the TC holder.

Since issuance of EASA AD 2010–0267, additional occurrences have been reported. The results of the investigations revealed that WTB fitted with brake plates manufactured by JURID (Part Number (P/N) 1007A0000–03, P/N 1007A0000–04, or P/N 1007A0000–05) are more sensitive to wear than those manufactured by MIBA (P/N 1007A0000–06 or P/N 1007B0000–01).

For the reason described above, this AD retains the requirements of EASA AD 2010– 0267, which is superseded, and requires:

• a repetitive Operational Test of the WTB/ POB performance on the flap and slat systems, and

• embodiment of the terminating action which consists in the installation of WTB standard build on brake plates manufactured by MIBA. 

### You may obtain further information by examining the MCAI in the AD docket.

Comments

We gave the public the opportunity to participate in developing this final rule. We received no comments on the NPRM (78 FR 29666, May 21, 2013) or on the determination of the cost to the public.

Conclusion

We reviewed the available data and determined that air safety and the public interest require adopting this final rule as proposed. Costs of Compliance

We estimate that this final rule affects 400 products of U.S. registry. We estimate that it takes about 7 work-hours per product to comply with the basic requirements of this final rule. Required parts would cost up to $2,422 per product. The average labor rate is $85 per work-hour. Based on these figures, we estimate the cost of this final rule on U.S. operators to be up to $1,206,800, or up to $3,017 per product. Paperwork Reduction Act

A federal agency may not conduct or sponsor, and a person is not required to respond to, nor shall a person be subject to penalty for failure to comply with a collection of information subject to the requirements of the Paperwork Reduction Act unless that collection of information displays a current valid OMB control number. The control number for the collection of information required by this AD is 2120–0056. The paperwork cost associated with this AD has been detailed in the Costs of Compliance section of this document and includes time for reviewing instructions, as well as completing and reviewing the collection of information. Therefore, all reporting associated with this AD is mandatory. Comments concerning the accuracy of this burden and suggestions for reducing the burden should be directed to the FAA at 800 Independence Ave. SW., Washington, DC 20591. ATTN: Information Collection Clearance Officer, AES–200. 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 final rule 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 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; 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


## 53637 Federal Register / Vol. 78, No. 169 / Friday, August 30, 2013 / Rules and Regulations

contains this AD, the MCAI, 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 adding the following new airworthiness directive (AD):

2013–17–03 Airbus: Amendment 39–17567; Docket No. FAA–2013–0422; Directorate Identifier 2012–NM–097–AD.
(a) Effective Date

This AD is effective October 4, 2013.
(b) Affected ADs

None. (c) Applicability

This AD applies to Airbus Model A330– 201, –202, –203, –223, –243, –223F, –243F, –301, –302, –303, –321, –322, –323, –341, –342, and –343 airplanes; Model A340–211, –212, –213, –311, –312, and –313 airplanes; and Model A340–541 and Model A340–642 airplanes; certificated in any category; all manufacturer serial numbers.
(d) Subject

Air Transport Association (ATA) of America Code 27, Flight controls.
(e) Reason

This AD was prompted by reports of wing tip brakes (WTBs) losing their braking function in service due to heavy wear on the brake discs. We are issuing this AD to detect and correct failure of the WTB and consequent loss of control 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) Part Number Determination

Within 30 days after the effective date of this AD: Inspect to determine the part number (P/N) of the four WTBs of the flap and slat systems, in accordance with the Instructions of Airbus Alert Operators Transmission (AOT) A27L001–12, Revision 01, dated April 27, 2012. A review of the Airbus airplane inspection report (AIR) or airplane maintenance records is acceptable to identify the part number of the WTB installed, provided that part number can be conclusively determined from that review.
(h) Repetitive Operational Tests

For any WTB having P/N 1007A0000–03, P/N 1007A0000–04, or P/N 1007A0000–05, as determined by paragraph (g) of this AD: At the later of the times specified in paragraphs (h)(1) and (h)(2) of this AD, and thereafter at intervals not to exceed 1,000 flight hours, perform an operational test of the WTB on the affected flap and/or slat systems in accordance with the Instructions of Airbus AOT A27L001–12, Revision 01, dated April 27, 2012.

(1) Within 1,000 flight hours since the last accomplishment of A330/A340 Maintenance Review Board Report (MRBR) tasks 27.50.00/ 14 and 27.80.00/10, or since first flight of the airplane, whichever occurs later.

(2) Within 30 days after the effective date of this AD.
(i) Replacement of WTBs That Fail the Operational Test

If any WTB operational test fails, before further flight, replace the affected WTB with a serviceable WTB, in accordance with the Instructions of Airbus AOT A27L001–12, Revision 01, dated April 27, 2012. Installation of a WTB having P/N 1007A0000–03, P/N 1007A0000–04, or P/N 1007A0000–05, does not constitute terminating action for the repetitive tests required by paragraph (h) of this AD.
(j) Replacement of WTBs

Within 26 months after the effective date of this AD, replace each WTB having P/N 1007A0000–03, P/N 1007A0000–04, or P/N 1007A0000–05 with a WTB having P/N 1007A0000–06, in accordance with the Instructions of Airbus AOT A27L001–12, Revision 01, dated April 27, 2012. Accomplishing the replacement required by this paragraph constitutes terminating action for the repetitive operational tests required by paragraph (h) of this AD.
(k) Optional Installation

As an alternative to accomplishing the replacement required by paragraph (j) of this AD, installation of a WTB having P/N 1007B0000–01, in accordance with the Instructions of Airbus AOT A27L001–12, Revision 01, dated April 27, 2012, is acceptable for compliance with the requirements of paragraph (j) of this AD and constitutes terminating action for the repetitive operational tests required by paragraph (h) of this AD.
(l) Parts Installation Prohibition and Limitation

(1) For airplanes on which Airbus Modification 43512 has been embodied in production: As of the effective date of this AD, installing a WTB having P/N 1007A0000–03, P/N 1007A0000–04, or P/N 1007A0000–05 is not allowed.

(2) For airplanes on which Airbus Modification 43512 has not been embodied in production: Installing a WTB having P/N 1007A0000–03, P/N 1007A0000–04, or P/N 1007A0000–05 is allowed; provided that after its installation the operational test is performed before further flight, and passed successfully, in accordance with the Instructions of Airbus AOT A27L001–12, Revision 01, dated April 27, 2012.
(m) Credit for Previous Actions

This paragraph provides credit for actions required by paragraphs (g), (h), (i), (j), and (k) of this AD, if those actions were performed before the effective date of this AD using Airbus AOT A27L001–12, dated April 26, 2012, which is not incorporated by reference in this AD.
(n) Reporting to Airbus

Submit a report of the initial identification of the part numbers of the WTBs required by paragraph (g) of this AD, and a report of the findings of each operational test required by paragraph (h) of this AD (both positive and negative), to Airbus, Customer Services, Engineering and Technical Support, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex France, Attn: Daniel Lopez-Fernandez, SEEL6; fax: (+33) 5 61 93 04 52; email: daniel.lopez-fernandez@airbus.com; at the applicable time specified in paragraph (n)(1) or (n)(2) of this AD.

(1) If the action was done on or after the effective date of this AD: Submit the report within 90 days after accomplishing the action.

(2) If the action was done before the effective date of this AD: Submit the report within 90 days after the effective date of this AD.
(o) 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: Vladimir Ulyanov, Aerospace Engineer, International Branch, ANM–116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, Washington 98057– 3356; telephone (425) 227–1138; 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) 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 FAA-approved 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.


## 53638 Federal Register / Vol. 78, No. 169 / Friday, August 30, 2013 / Rules and Regulations

(3) Reporting Requirements: A federal agency may not conduct or sponsor, and a person is not required to respond to, nor shall a person be subject to a penalty for failure to comply with a collection of information subject to the requirements of the Paperwork Reduction Act unless that collection of information displays a current valid OMB Control Number. The OMB Control Number for this information collection is 2120–0056. Public reporting for this collection of information is estimated to be approximately 5 minutes per response, including the time for reviewing Instructions, completing and reviewing the collection of information. All responses to this collection of information are mandatory. Comments concerning the accuracy of this burden and suggestions for reducing the burden should be directed to the FAA at: 800 Independence Ave. SW., Washington, DC 20591, Attn: Information Collection Clearance Officer,
AES–200.
(p) Related Information

(1) Refer to Mandatory Continuing Airworthiness Information, European Aviation Safety Agency Airworthiness Directive 2012–0082, dated May 15, 2012, for related information, which can be found in the AD docket on the Internet at http:// www.regulations.gov.

(2) Service information identified in this AD that is not incorporated by reference may be obtained at the addresses specified in paragraphs (q)(3) and (q)(4) of this AD.
(q) 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) Airbus Alert Operators Transmission A27L001–12, Revision 01, dated April 27,

2012.

(ii) Reserved. (3) For service information identified in this AD, contact Airbus SAS—Airworthiness Office—EAL, 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.airworth-eas@airbus.com; Internet http://www.airbus.com.

(4) 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.

(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 August 9, 2013. Jeffrey E. Duven, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service.
[FR Doc. 2013–20110 Filed 8–29–13; 8:45 am]

**BILLING CODE 4910–13–P**



### DEPARTMENT OF TRANSPORTATION

**Federal Aviation Administration**

**14 CFR Part 39**

**[Docket No. FAA–2013–0459; Directorate Identifier 2013–NM–044–AD; Amendment**  **39–17569; AD 2013–17–05]**

**RIN 2120–AA64**



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

**AGENCY** 

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

**ACTION** 

### : Final rule.

**SUMMARY** 

### : We are adopting a new airworthiness directive (AD) for certain Bombardier, Inc. Model CL–600–2C10 (Regional Jet Series 700, 701, & 702) airplanes, Model CL–600–2D15 (Regional Jet Series 705) airplanes, Model CL–600–2D24 (Regional Jet Series 900) airplanes, and Model CL– 600–2E25 (Regional Jet Series 1000) airplanes. This AD was prompted by reports of erratic pitch movement and oscillatory behaviors of the elevator control system. This AD requires repetitive replacement of the bellcrank supports on the inner rear spar of the horizontal stabilizer with new, improved bellcrank supports. We are issuing this AD to prevent erratic pitch movement and transient accelerations, which could result in a significant pitch upset, and injuries to passengers and flightcrew.

**DATES** 

### : This final rule becomes effective October 4, 2013.

The Director of the Federal Register approved the incorporation by reference of a certain publication listed in the AD as of October 4, 2013.

**ADDRESSES** 

### : You may examine the AD docket on the Internet at http:// www.regulations.gov or in person at the U.S. Department of Transportation, Docket Operations, M–30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE., Washington, DC.

**FOR FURTHER INFORMATION CONTACT** 

### : Ricardo Garcia, Aerospace Engineer, Airframe and Mechanical Systems Branch, ANE–171, FAA, New York Aircraft Certification Office, 1600 Stewart Avenue, Suite 410, Westbury, New York 11590; telephone (516) 228– 7331; fax (516) 794–5531.

**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 31, 2013 (78 FR 32579). The NPRM proposed to correct an unsafe condition for the specified products.

Transport Canada Civil Aviation (TCCA), which is the aviation authority for Canada, has issued Canadian Airworthiness Directive CF–2013–03, dated February 5, 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 several reported incidents of erratic pitch movements and oscillatory behaviors of the elevator control system. Investigation revealed that, the increase in the elevator breakout force induced by the introduction of a new elevator centering mechanism, in combination with the existing bracket assembly backlash and bearing friction of the bell crank support, could result in erratic pitch movement and oscillatory behavior of the elevator control system. This condition, if not corrected, could result in pitch upset of the aeroplane that generates transient accelerations. These accelerations could be high enough to injure aeroplane occupants that are not restrained in their
seats.

This [TCCA] AD mandates the repetitive replacement of the bellcrank supports with a new bearing.



### You may obtain further information by examining the MCAI in the AD docket.

Comments

We gave the public the opportunity to participate in developing this AD. We considered the comment received. The Airline Pilots Association International supported the NPRM (78 FR 32579, May 31, 2013).

Conclusion

We reviewed the available data, including the comment received, and determined that air safety and the public interest require adopting this final rule as proposed. Costs of Compliance

We estimate that this AD affects 400 products of U.S. registry. We also estimate that it takes about 7 work-hours per product to comply with the basic requirements of this AD. Required parts would cost up to $2,422 per product.