Federal Register / Vol. 78, No. 161 / Tuesday, August 20, 2013 / Rules and Regulations 51055 

on both balance weights is outside the date 

range of January 1, 1996, and December 31, 

2005, then no further action is required for 

this AD. 

(iii) For a replaced balance weight, if you 

cannot positively identify the date of 

purchase of a balance weight from Hawker 

Beechcraft Corporation (also known as 

Raytheon Aircraft Company or Beechcraft 

Corporation), then you must complete all of 

the actions in paragraph (h) and (i), all 

subparagraphs, as applicable in this AD. 

(2) For Model 58 airplanes, all serial 

numbers (except TH–1768 through TH– 

2110), and Models 58TC, 58P, 95–C55, E55, 

and 56TC airplanes, all serial numbers, 

before further flight after September 24, 2013 

(the effective date of this AD) review the 

airplane maintenance records to determine if 

the elevator balance weights have ever been 

replaced. An owner/operator (pilot) holding 

at least a private pilot certificate is allowed 

to do this action. 

(i) If, as a result of the maintenance records 

check, you positively identify that both of the 

elevator balance weights have never been 

replaced, then no further action is required 

for this AD. An owner/operator (pilot) 

holding at least a private pilot certificate is 

allowed to do this action. 

(ii) If, as a result of the maintenance 

records check, you identify that one or both 

of the balance weights have been replaced 

and you can positively identify by means of 

an Airworthiness Approval Tag (FAA Form 

8130–3) or other positive form of parts 

identification such as a shipping ticket, 

invoice, or direct ship authority letter, that 

the purchase date from Hawker Beechcraft 

Corporation (also known as Raytheon 

Aircraft Company or Beechcraft Corporation) 

is outside the date range of January 1, 1996, 

and December 31, 2005, then no further 

action is required for this AD. 

(iii) If you cannot positively identify the 

date of purchase of an aircraft balance weight 

from Hawker Beechcraft Corporation (also 

known as Raytheon Aircraft Company or 

Beechcraft Corporation), then you must 

perform all of the actions in paragraph (h) 

and (i), all subparagraphs, as applicable in 

this AD. 

(h) Inspection of Elevator Balance Weight 

Before further flight after September 24, 

2013 (the effective date of this AD) and 

thereafter at intervals not to exceed 100 hours 

time-in-service (TIS) until the replacement 

required by this AD is done, inspect the 

elevator balance weights for looseness, 

failure, and/or working (smoking) fasteners 

and inserts following the Accomplishment 

Instructions paragraph 3.A in Hawker 

Beechcraft Mandatory Service Bulletin SB 

55–4089, Revision 1, dated February, 2012. 

(i) Replacement of Elevator Balance Weight 

(1) Replace the defective elevator balance 

weight with an airworthy balance weight as 

specified in the Accomplishment 

Instructions paragraph 3.A in Hawker 

Beechcraft Mandatory Service Bulletin SB 

55–4089, Revision 1, dated February, 2012, at 

either paragraph (i)(1)(i) or (i)(1)(ii) of this 

AD, whichever occurs first: 

(i) Before further flight after any inspection 

required by paragraph (h) of this AD where 

any looseness, failure, and/or working 

(smoking) fasteners and inserts are found; or 

(ii) Within the next 200 hours TIS after 

September 24, 2013 (the effective date of this 

AD). 

(2) Replacement of elevator balance 

weights with airworthy elevator balance 

weights terminates the 100-hour inspection 

requirement in paragraph (h) of this AD. 

(3) As of September 24, 2013 (the effective 

date of this AD), do not install P/N 96– 

610022, P/N 96–61022–5, P/N 96–610022–7, 

and P/N 96–610022–9 elevator balance 

weight assemblies, if originally purchased 

from Hawker Beechcraft Corporation (also 

known as Raytheon Aircraft Company or 

Beechcraft Corporation) between January 1, 

1996, and December 31, 2005, on any 

airplane. 

(j) Special Flight Permit 

Special flight is permitted with the 

following limitations: Maximum structural 

cruising speed (Vno) = Design Speed for 

maximum gust intensity (Vb) = 195 Knots 

Calibrated Airspeed (KCAS), or 

Vno=Vb=195KCAS. This special flight is not 

allowed into known turbulence, and the 

duration of this flight should not be more 

than a total of 10 hours TIS. 

(k) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Wichita Aircraft 

Certification Office (ACO), 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 manager of the ACO, send it to the 

attention of the person identified in the 

Related Information section of this AD. 

(2) 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. 

(l) Related Information 

For more information about this AD, 

contact T. N. Baktha, Senior Aerospace 

Engineer, FAA, Wichita ACO, 1801 Airport 

Road, Room 100, Wichita, Kansas 67209; 

telephone: (316) 946–4155; fax: (316) 946– 

4107; email: t.n.baktha@faa.gov. 

(m) 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) Hawker Beechcraft Mandatory Service 

Bulletin SB 55–4089, Revision 1, dated 

February, 2012. 

(ii) Reserved. 

(3) For Beechcraft Corporation and Hawker 

Beechcraft Corporation service information 

identified in this AD, contact Beechcraft 

Corporation, B091–A04, 10511 E. Central 

Ave., Wichita, Kansas 67206; telephone: 1 

(800) 429–5372 or (316) 676–3140; fax: (316) 

676–8027; email: tmdc@beechcraft.com; or 

Internet: http://www.beechcraft.com/

customer_support/technical_and_field_

support/. 

(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/ibrlocations.html. 

Issued in Kansas City, Missouri, on July 25, 

2013. 

Earl Lawrence, 

Manager, Small Airplane Directorate, Aircraft 

Certification Service. 

[FR Doc. 2013–20098 Filed 8–19–13; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2013–0367; Directorate 

Identifier 2012–NM–177–AD; Amendment 

39–17546; AD 2013–16–08] 

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, and 

Model CL–600–2D24 (Regional Jet 

Series 900) airplanes. This AD was 

prompted by a report of corrosion of the 

components of the main landing gear 

(MLG) retraction actuator found in 

service; the corrosion was found at the 

interface of the rod end and the piston, 

and at the bracket and related pins. This 

AD requires inspection of the MLG 

retraction actuator components; 

corrective actions if necessary; and, for 

certain retraction actuators, installation 

of a new jam nut. We are issuing this 

AD to prevent disconnection of the MLG 

retraction actuator, which could result 

in extension of the MLG without 

damping, and consequent structural 

damage and collapse of the MLG during 

landing. 

DATES: This AD is effective September 

24, 2013. 


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51056 Federal Register / Vol. 78, No. 161 / Tuesday, August 20, 2013 / Rules and Regulations 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in the AD 

as of September 24, 2013. 

ADDRESSES: You may examine the AD 

docket on the Internet at http://

www.regulations.gov; or in person at 

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: 

Cesar Gomez, 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– 

7318; 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 10, 2013 (78 FR 27318). 

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–2011–36R1, 

dated October 3, 2012, the Mandatory 

Continuing Airworthiness Information 

(MCAI), to correct an unsafe condition 

for the specified products. The MCAI 

states: 

Corrosion of the main landing gear (MLG) 

retraction actuator components was found inservice, either at the interface of the rod end 

and the piston or at the bracket and its 

related pins. This can cause the MLG 

retraction actuator to disconnect, leading to 

an MLG extension without damping, and a 

potential for MLG structural damage and 

possible collapse during landing. 

This [Canadian] AD mandates the 

inspection and rectification [corrective 

action] of the MLG retraction actuator 

components. 

This revision is to mandate [, for certain 

MLG retraction actuators,] the installation of 

the new retraction actuator jam nut. This 

revision also corrects the background 

information and updates Service Bulletin 

(SB) references. 

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 

received no comments on the NPRM (78 

FR 27318, May 10, 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. 

Costs of Compliance 

Based on the service information, we 

estimate that this AD affects about 391 

products of U.S. registry. We also 

estimate that it takes up to 16 workhours 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 $1,018 

per product. Where the service 

information lists required parts costs 

that are covered under warranty, we 

have assumed that there will be no 

charge for these parts. As we do not 

control warranty coverage for affected 

parties, some parties may incur costs 

higher than estimated here. Based on 

these figures, we estimate the cost of 

this AD on U.S. operators to be up to 

$929,798, or up to $2,378 per product. 

We have received no definitive data 

that would enable us to provide cost 

estimates 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, 

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 

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. 

We prepared a regulatory evaluation 

of the estimated costs to comply with 

this AD and placed it in the AD docket. 

Examining the AD Docket 

You may examine the AD docket on 

the Internet at http://

www.regulations.gov; or in person at the 

Docket Operations office between 9 a.m. 

and 5 p.m., Monday through Friday, 

except Federal holidays. The AD docket 

contains this AD, the 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): 

2013–16–08 Bombardier, Inc.: Amendment 

39–17546; Docket No. FAA–2013–0367; 

Directorate Identifier 2012–NM–177–AD. 

(a) Effective Date 

This AD becomes effective September 24, 

2013. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to the airplanes specified 

in paragraphs (c)(1) and (c)(2) of this AD, 

certificated in any category. 

(1) Bombardier, Inc. Model CL–600–2C10 

(Regional Jet Series 700, 701, & 702) 

airplanes, serial numbers 10002 and 

subsequent. 


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Federal Register / Vol. 78, No. 161 / Tuesday, August 20, 2013 / Rules and Regulations 51057 

(2) Bombardier, Inc. Model CL–600–2D15 

(Regional Jet Series 705) and CL–600–2D24 

(Regional Jet Series 900) airplanes, serial 

numbers 15001 and subsequent. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 32: Landing gear. 

(e) Reason 

This AD was prompted by a report of 

corrosion of the components of the main 

landing gear (MLG) retraction actuator found 

in service; the corrosion was found at the 

interface of the rod end and the piston, and 

at the bracket and related pins. We are 

issuing this AD to prevent disconnection of 

the MLG retraction actuator, which could 

result in extension of the MLG without 

damping, and consequent structural damage 

and collapse of the MLG during 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) Inspection of the MLG Retraction 

Actuator and Corrective Actions 

For any airplane with an MLG retraction 

actuator assembly having any part number 

and serial number identified in paragraph 

1.A., Effectivity, of Bombardier Service 

Bulletin 670BA–32–031, Revision C, dated 

April 17, 2012, except airplanes on which 

modification status ‘‘32–64’’ is marked on the 

identification plate: At the applicable time 

specified in paragraph (g)(1) or (g)(2) of this 

AD, perform a detailed inspection of the 

retraction actuator assembly for evidence of 

corrosion and security of the jam nut, as 

applicable, in accordance with Part A of the 

Accomplishment Instructions of Bombardier 

Service Bulletin 670BA–32–031, Revision C, 

dated April 17, 2012; and Goodrich Service 

Bulletin 49600–32–63 R1, dated May 17, 

2011. If any corrosion or unsecured jam nut 

is found, before further flight, replace the 

retract actuator with a new or serviceable 

retract actuator; and install the retract 

actuator in accordance with Part A of the 

Accomplishment Instructions of Bombardier 

Service Bulletin 670BA–32–031, Revision C, 

dated April 17, 2012. Repeat the inspection 

at intervals not to exceed 1,200 flight hours 

or 12 months, whichever occurs first. 

(1) For MLG retraction actuator assemblies 

on which, as of the effective date of this AD, 

8,000 or more total flight hours have 

accumulated since new or since overhaul, or 

have been in service for more than 4 years 

since new or since overhaul: Inspect within 

1,200 flight hours or 12 months after the 

effective date of this AD, whichever occurs 

first. 

(2) For MLG retraction actuator assemblies 

on which, as of the effective date of this AD, 

less than 8,000 total flight hours have 

accumulated since new or since overhaul, 

and have been in service for 4 years or less 

since new or since overhaul: Inspect before 

the accumulation of 9,200 total flight hours 

on the MLG retraction actuator assembly 

since new or since overhaul or within 5 years 

in service since new or since overhaul, 

whichever occurs first. 

(h) Inspection of MLG Retraction Actuator 

Bracket and Related Pins, and Corrective 

Actions 

For any airplane with an MLG dressed 

shock strut having any part number and 

serial number identified in paragraph 1.A., 

Effectivity, of Bombardier Service Bulletin 

670BA–32–033, Revision B, dated June 26, 

2012: Within 4,400 flight hours or 24 months 

after the effective date of this AD, whichever 

occurs first, perform a detailed inspection of 

the retract actuator bracket assembly, 

associated pins, and the mating lugs on the 

outer cylinder for evidence of corrosion, in 

accordance with Bombardier Service Bulletin 

670BA–32–033, Revision B, dated June 26, 

2012; and Goodrich Service Bulletin 49000– 

32–46 R2, dated November 11, 2011. Do all 

applicable corrective actions before further 

flight (i.e., replace retract actuator bracket 

assembly and pins, or outer cylinder lugs, as 

applicable). 

(i) Installation of New Jam Nut 

For any airplane with an MLG retraction 

actuator assembly having any part number 

and serial number identified in paragraph 

1.A., Effectivity, of Bombardier Service 

Bulletin 670BA–32–031, Revision C, dated 

April 17, 2012, except airplanes on which 

modification status ‘‘32–64’’ is marked on the 

identification plate: Within 20,000 flight 

hours or 10 years after the effective date of 

this AD, whichever occurs first, install a new 

jam nut having part number 49606–5, in 

accordance with Part B of the 

Accomplishment Instructions of Bombardier 

Service Bulletin 670BA–32–031, Revision C, 

dated April 17, 2012; and Goodrich Service 

Bulletin 49600–32–64 R3, dated December 

15, 2011. 

(j) Credit for Previous Actions 

(1) This paragraph provides credit for the 

actions required by paragraphs (g) and (i) of 

this AD, if those actions were performed 

before the effective date of this AD using the 

service information specified in paragraphs 

(j)(1)(i), (j)(1)(ii), or (j)(1)(iii) of this AD, 

which is not incorporated by reference in this 

AD. 

(i) Bombardier Service Bulletin 670BA–32– 

031, dated March 14, 2011. 

(ii) Bombardier Service Bulletin 670BA– 

32–031, Revision A, dated June 9, 2011. 

(iii) Bombardier Service Bulletin 769BA– 

32–031, Revision B, dated July 29, 2011. 

(2) This paragraph provides credit for the 

actions required by paragraph (h) of this AD, 

if those actions were performed before the 

effective date of this AD using the service 

information specified in paragraph (j)(2)(i) or 

(j)(2)(ii) of this AD, which is not incorporated 

by reference in this AD. 

(i) Bombardier Service Bulletin 670BA–32– 

033, dated March 14, 2011. 

(ii) Bombardier Service Bulletin 670BA– 

32–033, Revision A, dated July 29, 2011. 

(k) Parts Installation Limitations 

(1) As of the effective date of this AD, no 

person may install on any airplane an MLG 

retraction actuator assembly having any part 

number and serial number identified in 

paragraph 1.A., Effectivity, of Bombardier 

Service Bulletin 670BA–32–031, Revision C, 

dated April 17, 2012, unless that retraction 

actuator assembly has been inspected as 

specified in paragraph (g) of this AD, and all 

applicable corrective actions (i.e., 

replacement of the retract actuator) specified 

in paragraph (g) of this AD have been done. 

Repeat the inspection specified in paragraph 

(g) of this AD thereafter at the intervals 

specified in paragraph (g) of this AD. 

(2) As of the effective date of this AD, no 

person may install on any airplane an MLG 

retraction actuator assembly having any part 

number and serial number identified in 

paragraph 1.A., Effectivity, of Bombardier 

Service Bulletin 670BA–32–033, Revision B, 

dated June 26, 2012, unless that retraction 

actuator assembly has been inspected and all 

applicable corrective actions have been done, 

in accordance with the Accomplishment 

Instructions of Bombardier Service Bulletin 

670BA–32–033, Revision B, dated June 26, 

2012. 

(l) 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, New York 

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. 

(m) Related Information 

(1) Refer to Mandatory Continuing 

Airworthiness Information Canadian 

Airworthiness Directive CF–2011–36R1, 

dated October 3, 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 address specified in 

paragraph (n)(3) of this AD. 

(n) 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. 


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51058 Federal Register / Vol. 78, No. 161 / Tuesday, August 20, 2013 / Rules and Regulations 

(2) You must use this service information 

as applicable to do the actions required by 

this AD, unless the AD specifies otherwise. 

(i) Bombardier Service Bulletin 670BA–32– 

031, Revision C, dated April 17, 2012. 

(ii) Bombardier Service Bulletin 670BA– 

32–033, Revision B, dated June 26, 2012. 

(iii) Goodrich Service Bulletin 49000–32– 

46 R2, dated November 11, 2011. 

(iv) Goodrich Service Bulletin 49600–32– 

63 R1, dated May 17, 2011. 

(v) Goodrich Service Bulletin 49600–32–64 

R3, dated December 15, 2011. 

(3) For Bombardier service information 

identified in this AD, contact Bombardier, 

Inc., 400 Coˆte-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. 

(4) For Goodrich service information 

identified in this AD, contact Goodrich 

Corporation, Landing Gear, 1400 South 

Service Road, West Oakville L6L 5Y7, 

Ontario, Canada; telephone 905–825–1568; 

email jean.breed@goodrich.com; Internet 

http://www.goodrich.com/TechPubs. 

(5) You may review copies of the service 

information at the FAA, Transport Airplane 

Directorate, 1601 Lind Avenue SW., Renton, 

Washington. For information on the 

availability of this material at the FAA, call 

425–227–1221. 

(6) 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 July 31, 

2013. 

Jeffrey E. Duven, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2013–20109 Filed 8–19–13; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2012–1038; Directorate 

Identifier 2011–NM–166–AD; Amendment 

39–17537; AD 2013–15–21] 

RIN 2120–AA64 

Airworthiness Directives; Airbus 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: We are superseding 

airworthiness directive (AD) 2004–13– 

06 for certain Airbus Model A319 and 

A320 series airplanes. AD 2004–13–06 

required repetitive detailed inspections 

to detect cracks in the keel beam side 

panels, and repair if necessary. This 

new AD requires repetitive eddy current 

inspections for cracking in the keel 

beam side panels, and corrective actions 

if necessary. This AD was prompted by 

reports of cracks on the side panels of 

the keel beams. We are issuing this AD 

to detect and correct fatigue cracks on 

the side panels of the keel beams, which 

could result in reduced structural 

integrity of the airplane. 

DATES: This AD becomes effective 

September 24, 2013. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of September 24, 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: 

Sanjay Ralhan, Aerospace Engineer, 

International Branch, ANM–116, 

Transport Airplane Directorate, FAA, 

1601 Lind Avenue SW., Renton, WA 

98057–3356; telephone (425) 227–1405; 

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 was published in the Federal 

Register on October 4, 2012 (77 FR 

60655), and proposed to supersede AD 

2004–13–06, Amendment 39–13688 (69 

FR 38818, June 29, 2004). 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 2011–0134, 

dated July 15, 2011 (referred to after this 

as ‘‘the MCAI’’), to correct an unsafe 

condition for the specified products. 

The MCAI states: 

During certification structural fatigue tests, 

several cases of structural damage (cracks) 

have been found on keel beam side panels. 

Cracks were observed on both sides of the 

keel beam around the rivets below the center 

wing box between frame (FR) 40 and FR 42, 

and in part of the area of the upper elliptical 

cut out forward of FR 41. 

This type of damage, if not detected and 

repaired, would adversely affect the 

structural integrity of the aeroplane. 

To address this unsafe condition, DGAC 

[Direction Ge ́ne ́rale de l’Aviation Civile] 

France issued AD 2003–146 [which 

corresponds to FAA AD 2004–13–06, 

Amendment 39–13688 (69 FR 38818, June 

29, 2004)] to require repetitive detailed 

inspections of those two areas and corrective 

actions, depending on findings. 

Prompted by reported access difficulties 

and to allow extension of the interval 

between two consecutive inspections, Airbus 

validated an Eddy current Non-Destructive 

Test (NDT) inspection to replace the detailed 

inspection. 

For the reasons described above, this 

[EASA] AD, which supersedes DGAC France 

AD 2003–146, requires repetitive Eddycurrent NDT inspections for cracks in the 

affected areas of the keel beam side panel 

below the center wing box and corrective 

actions [repair], depending on findings. 

You may obtain further information by 

examining the MCAI in the AD docket. 

Revised Service Information 

The NPRM (77 FR 60655, October 4, 

2012) referred to Airbus Mandatory 

Service Bulletin A320–53–1060, 

Revision 02, dated November 30, 2010, 

as the appropriate source of service 

information for the proposed actions. 

Airbus has revised this service 

information. We have reviewed Airbus 

Mandatory Service Bulletin A320–53– 

1060, Revision 04, dated September 13, 

2012, which includes an updated 

effectivity, an added illustration, 

amended job set-up and close-up 

procedures, and minor changes, but 

adds no accomplishment instruction 

procedures. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. We 

considered the comments received. 

Request To Revise Referenced Service 

Information 

Jetblue Airways requested that we 

revise the NPRM (77 FR 60655, October 

4, 2012) to reference the latest service 

information. 

We agree. As explained above, we 

reviewed Airbus Mandatory Service 

Bulletin A320–53–1060, Revision 04, 

dated September 13, 2012. We have 

revised this final rule to refer to Airbus 

Mandatory Service Bulletin A320–53– 

1060, Revision 04, dated September 13, 

2012; to add new paragraph (i) to allow 

credit for actions accomplished before 

the effective date of this AD using 

Airbus Mandatory Service Bulletin 

A320–53–1060, Revision 02, dated 

November 30, 2010, or Revision 03, 

dated January 20, 2012; and to reidentify subsequent paragraphs. 


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