Federal Register / Vol. 78, No. 211 / Thursday, October 31, 2013 / Rules and Regulations 65171 

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

Issued in Fort Worth, Texas, on September 

27, 2013. 

Lance T. Gant, 

Acting Directorate Manager, Rotorcraft 

Directorate, Aircraft Certification Service. 

[FR Doc. 2013–25312 Filed 10–30–13; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2013–0667; Directorate 

Identifier 2013–NM–062–AD; Amendment 

39–17639; AD 2013–22–07] 

RIN 2120–AA64 

Airworthiness Directives; The Boeing 

Company Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for certain 

The Boeing Company Model 747–400 

series airplanes. This AD was prompted 

by reports of fasteners missing on an 

airplane undergoing a passenger-tofreighter conversion. This AD requires 

doing a general visual inspection of the 

station 1920 splice clip for correct 

fastener installation, and related 

investigative and corrective actions if 

necessary. We are issuing this AD to 

detect and correct missing or incorrect 

fasteners, which can lead to cracking 

and loss of load carrying capacity, 

resulting in a possible decompression 

event. 

DATES: This AD is effective December 5, 

2013. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of December 5, 2013. 

ADDRESSES: For service information 

identified in this AD, contact Boeing 

Commercial Airplanes, Attention: Data 

& Services Management, P.O. Box 3707, 

MC 2H–65, Seattle, WA 98124–2207; 

telephone 206–544–5000, extension 1; 

fax 206–766–5680; Internet https://

www.myboeingfleet.com. You may view 

this referenced service information at 

the FAA, Transport Airplane 

Directorate, 1601 Lind Avenue SW., 

Renton, WA. For information on the 

availability of this material at the FAA, 

call 425–227–1221. 

Examining the AD Docket 

You may examine the AD docket on 

the Internet at http://

www.regulations.gov; or in person at the 

Docket Management Facility between 9 

a.m. and 5 p.m., Monday through 

Friday, except Federal holidays. The AD 

docket contains this AD, the regulatory 

evaluation, any comments received, and 

other information. The address for the 

Docket Office (phone: 800–647–5527) is 

Document Management Facility, U.S. 

Department of Transportation, Docket 

Operations, M–30, West Building 

Ground Floor, Room W12–140, 1200 

New Jersey Avenue SE., Washington, 

DC 20590. 

FOR FURTHER INFORMATION CONTACT: Bill 

Ashforth, Aerospace Engineer, Airframe 

Branch, ANM–120S, FAA, Seattle 

Aircraft Certification Office, 1601 Lind 

Avenue SW., Renton, WA 98057–3356; 

phone: 425–917–6432; fax: 425–917– 

6590; email: bill.ashforth@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 by adding an AD that would 

apply to the specified products. The 

NPRM published in the Federal 

Register on August 1, 2013 (78 FR 

46540). The NPRM proposed to require 

doing a general visual inspection of the 

station 1920 splice clip for correct 

fastener installation, and related 

investigative and corrective actions if 

necessary. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. We 

have considered the comment received. 

The Boeing Company supports the 

NPRM (78 FR 46540, August 1, 2013). 

Conclusion 

We reviewed the relevant data, 

considered the comment received, and 

determined that air safety and the 

public interest require adopting this AD 

as proposed—except for minor editorial 

changes. We have determined that these 

minor changes: 

• Are consistent with the intent that 

was proposed in the NPRM (78 FR 

46540, August 1, 2013) for correcting 

the unsafe condition; and 

• Do not add any additional burden 

upon the public than was already 

proposed in the NPRM (78 FR 46540, 

August 1, 2013). 

Costs of Compliance 

We estimate that this AD affects 3 

airplanes of U.S. registry. 

We estimate the following costs to 

comply with this AD: 

ESTIMATED COSTS

Action Labor cost Parts cost Cost per 

product 

Cost on U.S. 

operators 

Inspection for correct fastener installation ...... 2 work-hours × $85 per hour = $170 ............. $0 $170 $510 

We estimate the following costs to do 

any necessary repairs that would be 

required based on the results of the 

inspection. We have no way of 

determining the number of aircraft that 

might need these repairs: 

ON-CONDITION COSTS

Action Labor cost Parts cost Cost per 

product 

Inspections for cracking ................................................ 3 work-hours × $85 per hour = $255 ........................... $0 $255 

Fastener installation ..................................................... 2 work-hours × $85 per hour = $170 ........................... 0 170 

Repair ........................................................................... 2 work-hours × $85 per hour = $170 ........................... 0 170 

According to the manufacturer, some 

of the costs of this AD may be covered 

under warranty, thereby reducing the 

cost impact on affected individuals. We 

do not control warranty coverage for 

affected individuals. As a result, we 


wreier-aviles on DSK5TPTVN1PROD with RULES
65172 Federal Register / Vol. 78, No. 211 / Thursday, October 31, 2013 / Rules and Regulations 

have included all costs in our cost 

estimate. 

Authority for This Rulemaking 

Title 49 of the United States Code 

specifies the FAA’s authority to issue 

rules on aviation safety. Subtitle I, 

section 106, describes the authority of 

the FAA Administrator. Subtitle VII: 

Aviation Programs, describes in more 

detail the scope of the Agency’s 

authority. 

We are issuing this rulemaking under 

the authority described in Subtitle VII, 

Part A, Subpart III, Section 44701: 

‘‘General requirements.’’ Under that 

section, Congress charges the FAA with 

promoting safe flight of civil aircraft in 

air commerce by prescribing regulations 

for practices, methods, and procedures 

the Administrator finds necessary for 

safety in air commerce. This regulation 

is within the scope of that authority 

because it addresses an unsafe condition 

that is likely to exist or develop on 

products identified in this rulemaking 

action. 

Regulatory Findings 

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. 

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): 

2013–22–07 The Boeing Company: 

Amendment 39–17639; Docket No. 

FAA–2013–0667; Directorate Identifier 

2013–NM–062–AD. 

(a) Effective Date 

This AD is effective December 5, 2013. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to The Boeing Company 

Model 747–400 series airplanes, certificated 

in any category, as identified in Boeing Alert 

Service Bulletin 747–53A2844, Revision 1, 

dated July 30, 2012. 

(d) Subject 

Joint Aircraft System Component (JASC)/

Air Transport Association (ATA) of America 

Code 53, Fuselage. 

(e) Unsafe Condition 

This AD was prompted by reports of 

fasteners missing on an airplane undergoing 

a passenger-to-freighter conversion. We are 

issuing this AD to detect and correct missing 

or incorrect fasteners, which can lead to 

cracking and loss of load carrying capacity, 

resulting in a possible decompression event. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Inspection 

Except as required by paragraph (h)(1) of 

this AD, at the times specified in paragraph 

1.E., ‘‘Compliance,’’ of Boeing Alert Service 

Bulletin 747–53A2844, Revision 1, dated July 

30, 2012: Do a general visual inspection for 

correct installation of the station 1920 splice 

clip common to the auxiliary sill web and the 

tie clip, and do all applicable related 

investigative and corrective actions, in 

accordance with the Accomplishment 

Instructions of Boeing Alert Service Bulletin 

747–53A2844, Revision 1, dated July 30, 

2012, except as required by paragraph (h)(2) 

of this AD. Do all applicable related 

investigative and corrective actions before 

further flight. 

(h) Exceptions to the Service Information 

(1) Where Boeing Alert Service Bulletin 

747–53A2844, Revision 1, dated July 30, 

2012, specifies a compliance time ‘‘after the 

original issue date of the service bulletin,’’ 

this AD requires compliance within the 

specified compliance time after the effective 

date of this AD. 

(2) If any cracking is found during any 

inspection required by this AD, and Boeing 

Alert Service Bulletin 747–53A2844, 

Revision 1, dated July 30, 2012, specifies 

contacting Boeing for appropriate action: 

Before further flight, repair using a method 

approved in accordance with the procedures 

specified in paragraph (j) of this AD. 

(i) Credit for Previous Actions 

This paragraph provides credit for actions 

required by paragraph (g) of this AD, if those 

actions were performed before the effective 

date of this AD using Boeing Alert Service 

Bulletin 747–53A2844, dated September 15, 

2011, except the detailed inspection for 

cracking of the auxiliary sill outer chord tee 

and attached parts and all applicable related 

investigative and corrective actions must be 

done in accordance with Boeing Alert 

Service Bulletin 747–53A2844, Revision 1, 

dated July 30, 2012, at the times specified in 

paragraph (g) of this AD. Boeing Alert Service 

Bulletin 747–53A2844, dated September 15, 

2011, is not incorporated by reference in this 

AD. 

(j) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Seattle 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 

paragraph (k) of this AD. Information may be 

emailed to: 9-ANM-Seattle-ACO-AMOCRequests@faa.gov. 

(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. 

(3) An AMOC that provides an acceptable 

level of safety may be used for any repair 

required by this AD if it is approved by the 

Boeing Commercial Airplanes Organization 

Designation Authorization (ODA) that has 

been authorized by the Manager, Seattle ACO 

to make those findings. For a repair method 

to be approved, the repair must meet the 

certification basis of the airplane, and the 

approval must specifically refer to this AD. 

(k) Related Information 

(1) For more information about this AD, 

contact Bill Ashforth, Aerospace Engineer, 

Airframe Branch, ANM–120S, FAA, Seattle 

Aircraft Certification Office, 1601 Lind 

Avenue SW., Renton, WA 98057–3356; 

phone: 425–917–6432; fax: 425–917–6590; 

email: bill.ashforth@faa.gov. 

(2) Service information identified in this 

AD that is not incorporated by reference may 

be obtained at the addresses specified in 

paragraphs (i)(3) and (i)(4) of this AD. 

(l) 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) Boeing Alert Service Bulletin 747– 

53A2844, Revision 1, dated July 30, 2012. 

(ii) Reserved. 

(3) For service information identified in 

this AD, contact Boeing Commercial 


wreier-aviles on DSK5TPTVN1PROD with RULES
Federal Register / Vol. 78, No. 211 / Thursday, October 31, 2013 / Rules and Regulations 65173 

Airplanes, Attention: Data & Services 

Management, P.O. Box 3707, MC 2H–65, 

Seattle, WA 98124–2207; telephone 206– 

544–5000, extension 1; fax 206–766–5680; 

Internet https://www.myboeingfleet.com. 

(4) You may view this service information 

at 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 October 

17, 2013. 

Jeffrey E. Duven, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2013–25308 Filed 10–30–13; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2013–0543; Directorate 

Identifier 2012–NM–202–AD; Amendment 

39–17610; AD 2013–20–04] 

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 all 

Airbus Model A318, A319, A320, and 

A321 series airplanes. This AD was 

prompted by a determination that 

certain special washers used in the 

bearing installation of the retraction jack 

anchorage fitting in the main landing 

gear (MLG) were incorrectly 

manufactured. This AD requires an 

inspection of the left-hand (LH) and 

right-hand (RH) bearing assemblies of 

the MLG retraction jack anchorage 

fitting to verify that the special washer 

is seated correctly, and related 

investigative and corrective actions if 

necessary. We are issuing this AD to 

detect and correct installation of 

incorrectly manufactured special 

washers, which could lead to a local 

stress concentration resulting in 

possible reduction of the fatigue life of 

the jack fitting, and consequent 

reduction of the structural integrity of 

the affected MLG. 

DATES: This AD becomes effective 

December 5, 2013. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in this AD 

as of December 5, 2013. 

ADDRESSES: You may examine the AD 

on the Internet at http://

www.regulations.gov/

#!docketDetail;D=FAA-2013-0543; 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 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. You may review 

copies of the referenced service 

information at the FAA, Transport 

Airplane Directorate, 1601 Lind Avenue 

SW., Renton, WA. For information on 

the availability of this material at the 

FAA, call 425–227–1221. 

FOR FURTHER INFORMATION CONTACT: 

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 published in the Federal 

Register on July 1, 2013 (78 FR 39190). 

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 2012–0223, 

dated October 23, 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: 

Airbus identified a batch of special 

washers, Part Number (P/N) 

D5725260120000 and P/N D5725664320000, 

which were incorrectly manufactured and 

delivered as spares from the supplier 

between October 2006 and January 2010. As 

a result of these manufacturing defects, the 

affected washers differ geometrically from 

the design specifications. The results of 

further analyses on Airbus A318, A319, A320 

and A321 aeroplanes demonstrate that the 

affected washers could be seated incorrectly 

when installed on aeroplanes, which could 

affect the main landing gear (MLG) retraction 

jack anchorage fitting bearing installation. 

This condition, if not detected and 

corrected, could lead to a local stress 

concentration which may reduce the fatigue 

life of the jack fitting, possibly reducing the 

structural integrity of the affected MLG. 

For the reasons described above, this 

[EASA] AD requires a one-time detailed 

visual inspection of the left-hand (LH) and 

right-hand (RH) MLG retraction jack 

anchorage fitting bearing assemblies to verify 

that the special washer is seated correctly 

and, depending on findings, the 

accomplishment of applicable [related 

investigative action and] corrective actions. 

The related investigative action is a 

detailed inspection of the jack 

anchorage fitting for damage, corrosion, 

cracks or other defects. Corrective 

actions include replacing the special 

washer with a new special washer and 

repairing the jack anchorage fitting if 

there are signs of damage, corrosion, or 

other defects. You may examine the 

MCAI in the AD docket on the Internet 

at http://www.regulations.gov/

#!documentDetail;D=FAA-2013-0543- 

0003. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. We 

considered the comment received. The 

commenter, Jeremy Schreck, supported 

the NPRM (78 FR 39190, July 1, 2013). 

Conclusion 

We reviewed the available data, 

including the comment received, and 

determined that air safety and the 

public interest require adopting this AD 

as proposed—except for minor editorial 

changes. We have determined that these 

minor changes: 

• Are consistent with the intent that 

was proposed in the NPRM (78 FR 

39190, July 1, 2013) for correcting the 

unsafe condition; and 

• Do not add any additional burden 

upon the public than was already 

proposed in the NPRM (78 FR 39190, 

July 1, 2013). 

Costs of Compliance 

We estimate that this AD affects 851 

airplanes of U.S. registry. 

We estimate the following costs to 

comply with this AD: 


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