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

(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 


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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 specific 

failure 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 


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

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. 


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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. 


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