52414 Federal Register / Vol. 78, No. 164 / Friday, August 23, 2013 / Rules and Regulations 

(d) Compliance 

You are responsible for performing each 

action required by this AD within the 

specified compliance time unless it has 

already been accomplished prior to that time. 

(e) Required Actions 

Within 300 hours time-in-service: 

(1) Inspect the rigging of the power-boosted 

control system, referencing Figure 1 of 

Eurocopter Alert Service Bulletin ASB MBB 

BK117 C–2–67A–012, Revision 0, dated 

September 20, 2010 (ASB). Ensure the piston 

of the longitudinal actuator (right-hand side) 

is held in the fully extended position and the 

piston of the lateral actuator (left-hand side) 

is held in the fully retracted position against 

the mechanical stop. Also, ensure the gauge 

block is clamped between the sliding sleeve 

and the support tube. 

(2) Insert the rigging wedges with the 25.4 

degree (item 8 of Figure 1 of the ASB) and 

19.5 degree (item 7 of Figure 1 of the ASB) 

markings in the ‘‘A’’ side of the guide grooves 

of the rigging device (item 3 of Figure 1 of 

the ASB). 

(3) If the gap between the rigging wedges 

(items 7 and 8 of Figure 1 of the ASB) and 

the inner sleeves (item 9 of Figure 1 of the 

ASB) is closed, the rigging is correct. 

(4) If there is a nonparallel gap between the 

rigging wedges (items 7 and 8 of Figure 1 of 

the ASB) and the inner sleeves (item 9 of 

Figure 1 of the ASB), the rigging is not 

correct. Perform a rigging procedure. 

(f) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Safety Management 

Group, FAA, may approve AMOCs for this 

AD. Send your proposal to: Jim Grigg, 

Manager, Rotorcraft Directorate, 2601 

Meacham Blvd., Fort Worth, TX 76137, 

telephone (817) 222–5110, email Jim.Grigg@

faa.gov. 

(2) For operations conducted under 14 CFR 

part 119 operating certificate or under 14 

CFR part 91, subpart K, we suggest that you 

notify your principal inspector, or lacking a 

principal inspector, the manager of the local 

flight standards district office or certificate 

holding district office before operating any 

aircraft complying with this AD through an 

AMOC. 

(g) Additional Information 

(1) For service information identified in 

this AD, contact American Eurocopter 

Corporation, 2701 N. Forum Drive, Grand 

Prairie, TX 75052, telephone (972) 641–0000 

or (800) 232–0323, fax (972) 641–3775, or at 

http://www.eurocopter.com/techpub. You 

may review the referenced service 

information at the FAA, Office of the 

Regional Counsel, Southwest Region, 2601 

Meacham Blvd., Room 663, Fort Worth, 

Texas 76137. 

(2) The subject of this AD is addressed in 

European Aviation Safety Agency (EASA) AD 

No. 2010–0248, dated November 26, 2010. 

You may view the EASA AD at http://

www.regulations.gov in Docket No. FAA– 

2013–0020. 

(h) Subject 

Joint Aircraft Service Component (JASC) 

Code: 6710 Main Rotor Control. 

(i) Material Incorporated by Reference 

(1) The Director of the Federal Register 

approved the incorporation by reference 

(IBR) of the service information listed in this 

paragraph under 5 U.S.C. 552(a) and 1 CFR 

part 51. 

(2) You must use this service information 

as applicable to do the actions required by 

this AD, unless the AD specifies otherwise. 

(i) Eurocopter Alert Service Bulletin ASB 

MBB BK117 C–2–67A–012, Revision 0, dated 

September 20, 2010. 

(ii) Reserved. 

(3) For Eurocopter service information 

identified in this AD, contact American 

Eurocopter Corporation, 2701 N. Forum 

Drive, Grand Prairie, TX 75052, telephone 

(972) 641–0000 or (800) 232–0323, fax (972) 

641–3775, or at http://www.eurocopter.com/ 

techpub. 

(4) You may view this service information 

that is incorporated by reference at http://

www.regulations.gov in Docket No. FAA– 

2013–0020. 

(5) You may view this service information 

that is incorporated by reference at the 

National Archives and Records 

Administration (NARA). For information on 

the availability of this material at NARA, call 

(202) 741–6030, or go to: http://

www.archives.gov/federal-register/cfr/ibrlocations.html. 

Issued in Fort Worth, Texas, on August 2, 

2013. 

Lance T. Gant, 

Acting Manager, Rotorcraft Directorate, 

Aircraft Certification Service. 

[FR Doc. 2013–19443 Filed 8–22–13; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2012–1076; Directorate 

Identifier 2011–NM–274–AD; Amendment 

39–17556; AD 2013–16–18] 

RIN 2120–AA64 

Airworthiness Directives; Airbus 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for certain 

Airbus Model A320–214, –232 and –233 

airplanes; and Model A321–211, –213, 

and –231 airplanes. This AD was 

prompted by a report of a missing 

fastener between certain stringers of the 

fuselage frame that connects the frame 

to a tee. This AD requires an inspection 

for a missing fastener, and a rototest 

inspection and a modification or repair 

of the fuselage frame at the affected area 

if necessary. We are issuing this AD to 

detect and correct cracking in the 

fuselage that could result in reduced 

structural integrity of the airplane. 

DATES: This AD becomes effective 

September 27, 2013. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of September 27, 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 16, 2012 (77 FR 

63270). The NPRM proposed to correct 

an unsafe condition for the specified 

products. The European Aviation Safety 

Agency (EASA), which is the aviation 

authority for the Member States of the 

European Community, has issued EASA 

Airworthiness Directive 2011–0229, 

dated December 6, 2011 (referred to 

after this as ‘‘the MCAI’’), to correct an 

unsafe condition for the specified 

products. The MCAI states: 

During a quality check in production of an 

A320 family aeroplane, it was discovered 

that a fastener was missing at [frame] FR 24 

between stringer (STRG) 25 and STRG 26 on 

the right-hand (RH) side. The purpose of the 

missing fastener, a 4 [millimeter] mm 

diameter aluminum rivet, Part Number (P/N) 

ASNA2050DXJ040, is to connect the FR 24 to 

the FR 24 Tee. The hole where the fastener 

was missing was not drilled. 

Further investigations revealed that the 

drilling was missing on the milling grid used 

for frame assembly of a limited group of 

aeroplanes. 

This condition, if not corrected, could 

impair the structural integrity of the affected 

aeroplanes. 

For the reasons described above, this 

[EASA] AD requires a special detailed 

inspection (SDI) [rototest inspection for 

cracking] of the affected area, and the 

accomplishment of the associated corrective 

actions [modification and/or repair]. 

You may obtain further information by 

examining the MCAI in the AD docket. 


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Federal Register / Vol. 78, No. 164 / Friday, August 23, 2013 / Rules and Regulations 52415 

Comments 

We gave the public the opportunity to 

participate in developing this AD. We 

considered the comment received. 

Request To Include Latest Revision of 

Service Information 

Airbus requested that we revise the 

NPRM (77 FR 63270, October 16, 2012) 

to reflect the latest revision of the 

service information to add an inspection 

for a missing fastener that is included in 

that revised service information. Airbus 

stated that the rototest inspection is 

required only when it is confirmed that 

the fastener is missing. 

We agree with the commenter’s 

request. Airbus has issued Airbus 

Mandatory Service Bulletin A320–53– 

1247, Revision 01, dated October 15, 

2012. That service bulletin was revised 

to include procedures for a general 

visual inspection for a missing fastener. 

For airplanes on which no fastener is 

missing, the rototest inspection would 

no longer be necessary. We have 

changed paragraph (g) of this final rule 

to provide instructions for 

accomplishing the general visual 

inspection, which if accomplished and 

no fastener is missing, would eliminate 

the need for the rototest inspection. We 

have included the repair and 

modification that were part of paragraph 

(g) of the NPRM (77 FR 63270, October 

16, 2012) as new paragraph (h) of this 

final rule and changed subsequent 

identifiers accordingly. 

Conclusion 

We reviewed the available data, 

including the comment received, and 

determined that air safety and the 

public interest require adopting this AD 

with the changes described previously— 

and minor editorial changes. We have 

determined that these changes: 

• Are consistent with the intent that 

was proposed in the NPRM (77 FR 

63270, October 16, 2012) for correcting 

the unsafe condition; and 

• Do not add any additional burden 

upon the public than was already 

proposed in the NPRM (77 FR 63270, 

October 16, 2012). 

Costs of Compliance 

We estimate that this AD will affect 

111 products of U.S. registry. We also 

estimate that it will take about 6 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 $85 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 

to the U.S. operators to be $66,045, or 

$595 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. We have no way 

of determining the number of products 

that may need these actions. 

Authority for This Rulemaking 

Title 49 of the United States Code 

specifies the FAA’s authority to issue 

rules on aviation safety. Subtitle I, 

section 106, describes the authority of 

the FAA Administrator. ‘‘Subtitle VII: 

Aviation Programs,’’ describes in more 

detail the scope of the Agency’s 

authority. 

We are issuing this rulemaking under 

the authority described in ‘‘Subtitle VII, 

Part A, Subpart III, Section 44701: 

General requirements.’’ Under that 

section, Congress charges the FAA with 

promoting safe flight of civil aircraft in 

air commerce by prescribing regulations 

for practices, methods, and procedures 

the Administrator finds necessary for 

safety in air commerce. This regulation 

is within the scope of that authority 

because it addresses an unsafe condition 

that is likely to exist or develop on 

products identified in this rulemaking 

action. 

Regulatory Findings 

We determined that this AD will not 

have federalism implications under 

Executive Order 13132. This AD will 

not have a substantial direct effect on 

the States, on the relationship between 

the national government and the States, 

or on the distribution of power and 

responsibilities among the various 

levels of government. 

For the reasons discussed above, I 

certify that this AD: 

1. Is not a ‘‘significant regulatory 

action’’ under Executive Order 12866; 

2. Is not a ‘‘significant rule’’ under the 

DOT Regulatory Policies and Procedures 

(44 FR 11034, February 26, 1979); 

3. Will not affect intrastate aviation in 

Alaska; and 

4. Will not have a significant 

economic impact, positive or negative, 

on a substantial number of small entities 

under the criteria of the Regulatory 

Flexibility Act. 

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 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 AD: 

2013–16–18 Airbus: Amendment 39–17556. 

Docket No. FAA–2012–1076; Directorate 

Identifier 2011–NM–274–AD. 

(a) Effective Date 

This airworthiness directive (AD) becomes 

effective September 27, 2013. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to Airbus Model A320– 

214, –232, and –233 airplanes; and Model 

A321–211, –213, and –231 airplanes; 

certificated in any category; manufacturer 

serial numbers 4338, 4371, 4374, 4375, 4377, 

4381 through 4384 inclusive, 4386, 4387, 

4388, 4390 through 4402 inclusive, 4404 

through 4409 inclusive, 4411 through 4417 

inclusive, 4419, 4420, 4421, 4423, 4424, 

4426, 4429 through 4436 inclusive, 4438 

through 4443 inclusive, 4445 through 4450 

inclusive, 4453, 4454, 4456 through 4469 

inclusive, 4471, 4472, 4474 through 4481 

inclusive, 4483 through 4498 inclusive, 4500, 

4504, 4505, 4506, and 4509. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 53, Fuselage. 

(e) Reason 

This AD was prompted by a report of a 

missing fastener between certain stringers of 

the fuselage frame that connects the frame to 

a tee. We are issuing this AD to detect and 

correct cracking in the fuselage that could 

result in reduced structural integrity of the 

airplane. 


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52416 Federal Register / Vol. 78, No. 164 / Friday, August 23, 2013 / Rules and Regulations 

(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) Inspections 

Before the accumulation of 24,000 total 

flight cycles since first flight of the airplane, 

or within 30 days after the effective date of 

this AD, whichever occurs later, do the 

actions specified in paragraph (g)(1) or (g)(2) 

of this AD. 

(1) Do a general visual inspection for a 

missing fastener between the two fasteners at 

fuselage frame (FR) 24 between stringer 25 

and stringer 26 right-hand side, in 

accordance with the Accomplishment 

Instructions of Airbus Mandatory Service 

Bulletin A320–53–1247, Revision 01, dated 

October 15, 2012. 

(i) If the fastener is not missing, no further 

action is required by paragraph (g) of this AD. 

(ii) If the fastener is missing, before further 

flight, do the actions required by paragraph 

(g)(2) of this AD. 

(2) Do a rototest inspection for cracking of 

the two adjacent fastener holes at 

fuselage FR 24 between stringer 25 and 

stringer 26 right-hand side, in accordance 

with the Accomplishment Instructions of 

Airbus Service Bulletin A320–53–1247, 

dated July 15, 2011; or Airbus Mandatory 

Service Bulletin A320–53–1247, Revision 01, 

dated October 15, 2012. 

(h) Repair 

(1) If, during the rototest inspection 

specified by paragraph (g)(2) of this AD, any 

crack is found, before further flight, repair 

using a method approved by the Manager, 

International Branch, ANM–116, Transport 

Airplane Directorate, FAA; or the European 

Aviation Safety Agency (EASA) (or its 

delegated agent). 

(2) If, during the rototest inspection 

specified by paragraph (g)(2) of this AD, no 

crack is found, before the accumulation of 

24,000 total flight cycles since first flight of 

the airplane, or within 30 days after the 

effective date of this AD, whichever occurs 

later: Modify fuselage FR 24 between stringer 

25 and stringer 26 right-hand side, in 

accordance with the Accomplishment 

Instructions of Airbus Service Bulletin A320– 

53–1247, dated July 15, 2011; or Airbus 

Mandatory Service Bulletin A320–53–1247, 

Revision 01, dated October 15, 2012. 

(i) Other FAA AD Provisions 

The following provisions also apply to this 

AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, International 

Branch, ANM–116, 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: 

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. 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. 

(j) Related Information 

Refer to mandatory continuing 

airworthiness information (MCAI) EASA 

Airworthiness Directive 2011–0229, dated 

December 6, 2011, for related information. 

The MCAI may be viewed on the Internet at 

http://ad.easa.europa.eu/ad/2011–0229. 

EASA ADs are at http://ad.easa.europa.eu/. 

(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 the AD specifies otherwise. 

(i) Airbus Mandatory Service Bulletin 

A320–53–1247, Revision 01, dated October 

15, 2012. 

(ii) Airbus Service Bulletin A320–53–1247, 

dated July 15, 2011. 

(3) For service information identified in 

this AD, contact Airbus, Airworthiness 

Office—EIAS, 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.airwortheas@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 

2, 2013. 

Jeffrey E. Duven, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2013–19459 Filed 8–22–13; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2013–0092; Directorate 

Identifier 2012–NM–067–AD; Amendment 

39–17560; AD 2013–16–22] 

RIN 2120–AA64 

Airworthiness Directives; Embraer S.A. 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for certain 

Embraer S.A. Model ERJ 170 and ERJ 

190 airplanes. This AD was prompted 

by reports of chafing between the 

auxiliary power unit (APU) electronic 

starter controller (ESC) power cables 

and the airplane tail cone firewall. This 

AD requires a detailed inspection for 

damage to the insulation and inner 

conductors of the APU ESC power 

cables, installing a new grommet 

support in the tail cone firewall, and 

corrective actions if necessary. We are 

issuing this AD to detect and correct 

damage to the APU ESC power cable 

harness, which if not corrected, could 

result in reduced structural integrity of 

the fuselage and empennage in the event 

of fire penetration through the firewall. 

DATES: This AD becomes effective 

September 27, 2013. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in this AD 

as of September 27, 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: 

Cindy Ashforth, Aerospace Engineer, 

International Branch, ANM–116, 

Transport Airplane Directorate, FAA, 

1601 Lind Avenue SW., Renton, WA 

98057–3356; telephone (425) 227–2768; 

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. That 

NPRM was published in the Federal 

Register on February 22, 2013 (78 FR 


emcdonald on DSK67QTVN1PROD with RULES