Federal Register / Vol. 78, No. 208 / Monday, October 28, 2013 / Rules and Regulations 64159 

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, WA 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. 

(k) Related Information 

(1) Refer to Mandatory Continuing 

Airworthiness Information (MCAI) European 

Aviation Safety Agency (EASA) 

Airworthiness Directive 2012–0021, dated 

January 30, 2012, for related information. 

You may examine the MCAI on the Internet 

at http://www.regulations.gov by searching 

for and locating it in Docket No. FAA–2013– 

0832. 

(2) Service information identified in this 

AD that is not incorporated by reference may 

be obtained at the addresses specified in 

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

(l) Material Incorporated by Reference 

(1) The Director of the Federal Register 

approved the incorporation by reference 

(IBR) of the following service information 

under 5 U.S.C. 552(a) and 1 CFR part 51. 

(2) You must use the following service 

information to do the actions required by this 

AD, unless the AD specifies otherwise. 

(i) A340 Airworthiness Limitations Section 

(ALS), Part 4—Aging Systems Maintenance, 

Revision 02, dated October 12, 2011. The 

revision date is not identified on the title 

page of this document. 

(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 45 80; email 

airworthiness.A330-A340@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, 

Washington. For information on the 

availability of this material at the FAA, call 

425–227–1221. 

(5) You may also review copies of the 

service information that is incorporated by 

reference at the National Archives and 

Records Administration (NARA). For 

information on the availability of this 

material at an NARA facility, call 202–741– 

6030, or go to http://www.archives.gov/

federal_register/code_of_federal_regulations/

ibr_locations.html. 

Issued in Renton, Washington, on 

September 17, 2013. 

Ross Landes, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2013–23899 Filed 10–25–13; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2013–0539; Directorate 

Identifier 2012–NM–145–AD; Amendment 

39–17616; AD 2013–20–10] 

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) 2000–12– 

11, for certain Model A300 B4–600 and 

Model A300 B4–600R series airplanes. 

AD 2000–12–11 required repetitive 

inspections to detect cracks in the bolt 

holes inboard and outboard of rib 9 on 

the bottom booms of the front and rear 

wing spars, and repair if necessary. This 

new AD reduces the initial inspection 

compliance time and repetitive 

inspection interval. This AD was 

prompted by a fleet survey and an 

updated fatigue and damage tolerance 

analysis indicating a high risk for 

fatigue cracking on the front and rear 

spar bottom booms. We are issuing this 

AD to detect and correct fatigue cracks 

in the bolt holes of the wing spars, 

which could result in reduced structural 

integrity of a wing spar. 

DATES: This AD becomes effective 

December 2, 2013. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of December 2, 2013. 

ADDRESSES: You may examine the AD 

docket on the Internet at http://

www.regulations.gov/

#!docketDetail;D=FAA-2013-0539; 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 SAS—EAW 

(Airworthiness Office), 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. You 

may view this 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: Dan 

Rodina, Aerospace Engineer, 

International Branch, ANM–116, 

Transport Airplane Directorate, FAA, 

1601 Lind Avenue SW., Renton, WA 

98057–3356; phone: (425) 227–2125; 

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 3, 2013 (78 FR 40069), 

and proposed to supersede AD 2000– 

12–11, Amendment 39–11789 (65 FR 

37853, June 19, 2000). 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 2012–0138, 

dated July 26, 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: 

Full fatigue tests carried out by the 

manufacturer revealed crack initiation from 

the bolts holes at inboard and outboard of rib 

9, on the front and rear spar bottom booms. 

Similar cracks at the same area were reported 

by A300–600 aeroplane operators. 

This condition, if not detected and 

corrected, could affect the structural integrity 

of the aeroplane. 

To address this unsafe condition, 

[Direction Ge ́ne ́rale de l’Aviation Civile] 

DGAC France issued AD 94–208–169(B)R2 

(http://ad.easa.europa.eu/blob/19942082tb_

superseded.pdf/AD_F-1994-208-169R2_2) 

[which corresponds to FAA AD 95–07–05, 

Amendment 39–9187 (60 FR 17990, April 10, 

1995)] to require an ultrasonic inspection of 

holes inboard and outboard of rib 9 on the 

front and rear spar bottom booms on Left 

Hand and Right Hand wings. 

Since that [DGAC] AD was issued, a fleet 

survey and updated Fatigue and Damage 


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Tolerance analysis have been performed in 

order to substantiate the second A300–600 

Extended Service Goal (ESG2) exercise. The 

results of these analyses have shown that the 

risk for these aeroplanes is higher than 

initially determined and that, consequently, 

the inspection threshold and interval must be 

reduced to allow timely detection of cracks 

and the accomplishment of an applicable 

corrective action [and related investigative 

action]. 

For the reasons explained above, this new 

[EASA] AD retains the requirements of DGAC 

France AD 94–208–169(B)R2, which is 

superseded, and requires the 

accomplishment instructions within the new 

thresholds and intervals specified in 

Revision 04 of Airbus Mandatory Service 

Bulletin (SB) A300–57–6037 [dated February 

24, 2011]. 

The related investigative action includes 

doing inspections for cracking. The 

corrective actions include oversizing 

holes and installing new fasteners, and 

for certain conditions, contacting the 

FAA or EASA (or its delegated agent) for 

instructions. You may examine the 

MCAI in the AD docket on the Internet 

at http://www.regulations.gov/

#!documentDetail;D=FAA-2013-0539- 

0002. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. We 

received no comments on the NPRM (78 

FR 40069, July 3, 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 AD 

as proposed—except for minor editorial 

changes and re-formatting of the 

estimates cost data. The estimated cost 

data has not been changed. We have 

determined that these minor changes: 

• Are consistent with the intent that 

was proposed in the NPRM (78 FR 

40069, July 3, 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 40069, 

July 3, 2013). 

Costs of Compliance 

We estimate that this AD affects 29 

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 [new action] .......... 18 work-hours × $85 per hour 

= $1,530 [per inspection 

cycle].

$0 $1,530 [per inspection cycle] $44,370 [per inspection 

cycle]. 

We have received no definitive data 

that would enable us to provide cost 

estimates for the on-condition workhours specified in this AD. The oncondition parts cost estimate is $2,874. 

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 

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 

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/

#!docketDetail;D=FAA-2013-0539; 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 

removing airworthiness directive (AD) 

2000–12–11, Amendment 39–11789 (65 

FR 37853, June 19, 2000), and adding 

the following new AD: 

2013–20–10 Airbus: Amendment 39–17616. 

Docket No. FAA–2013–0539; Directorate 

Identifier 2012–NM–145–AD. 

(a) Effective Date 

This airworthiness directive (AD) becomes 

effective December 2, 2013. 

(b) Affected ADs 

This AD supersedes AD 2000–12–11, 

Amendment 39–11789 (65 FR 37853, June 

19, 2000). 


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(c) Applicability 

This AD applies to Airbus Model A300 B4– 

601, B4–603, B4–620, B4–622, B4–605R, and 

B4–622R airplanes; certificated in any 

category; all manufacturer serial numbers, 

except airplanes on which Airbus 

Modification 10161 has been incorporated in 

production. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 57, Wings. 

(e) Reason 

This AD was prompted by a fleet survey 

and an updated fatigue and damage tolerance 

analysis indicating a high risk for fatigue 

cracking on the front and rear spar bottom 

booms. We are issuing this AD to detect and 

correct fatigue cracks in the bolt holes of the 

wing spars, which could result in reduced 

structural integrity of a wing spar. 

(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) Repetitive Inspections 

At the applicable time specified in 

paragraph (g)(1) or (g)(2) of this AD: Perform 

an ultrasonic inspection to detect fatigue 

cracking of the bolt holes inboard and 

outboard of rib 9 on the bottom booms of the 

front and rear wing spars, in accordance with 

the Accomplishment Instruction of Airbus 

Mandatory Service Bulletin A300–57–6037, 

Revision 04, dated February 24, 2011, except 

as specified in paragraph (k) of this AD. 

Repeat the inspection thereafter at intervals 

not to exceed the applicable time specified in 

paragraph (h) of this AD. 

(1) For normal range airplanes, at the later 

of the times in paragraphs (g)(1)(i) and 

(g)(1)(ii) of this AD. 

(i) Within 14,100 flight cycles or 30,400 

flight hours since airplane first flight or 

within 14,100 flight cycles or 30,400 flight 

hours since airplane modification done as 

specified in the Accomplishment 

Instructions of Airbus Service Bulletin A300– 

57–6039 (which is not incorporated by 

reference in this AD), whichever occurs first. 

(ii) Within 1,600 flight cycles or 3,400 

flight hours, whichever occurs first after the 

effective date of this AD. 

(2) For short range airplanes, at the later of 

the times in paragraphs (g)(2)(i) and (g)(2)(ii) 

of this AD. 

(i) Within 15,200 flight cycles or 22,800 

flight hours since airplane first flight, or 

since airplane modification done as specified 

in the Accomplishment Instructions of 

Airbus Service Bulletin A300–57–6039 

(which is not incorporated by reference in 

this AD), whichever occurs first. 

(ii) Within 1,700 flight cycles or 2,500 

flight hours, whichever occurs first after the 

effective date of this AD. 

(h) Repetitive Inspection Compliance Times 

At the applicable time specified in 

paragraph (h)(1) or (h)(2) of this AD, repeat 

the inspection required by paragraph (g) of 

this AD. 

(1) For normal range airplanes: Repeat the 

inspection thereafter at intervals not to 

exceed 3,900 flight cycles or 8,400 flight 

hours, whichever occurs first. 

(2) For short range airplanes: Repeat the 

inspection thereafter at intervals not to 

exceed 4,200 flight cycles or 6,300 flight 

hours, whichever occurs first. 

(i) Corrective Action for Cracking 

If any crack is found during any inspection 

required by paragraph (g) of this AD: Before 

further flight, repair the cracking including 

applicable related investigative and 

corrective actions, in accordance with the 

Accomplishment Instructions of Airbus 

Mandatory Service Bulletin A300–57–6037, 

Revision 04, dated February 24, 2011, except 

as specified in paragraph (k) of this AD. Do 

related investigative and corrective actions 

before further flight. Thereafter, repeat the 

inspection required by paragraph (g) of this 

AD at intervals not to exceed the applicable 

time specified in paragraph (h) of this AD. 

Corrective actions required by this paragraph 

do not constitute terminating action for the 

repetitive inspections required by paragraph 

(h) of this AD. 

(j) Definition of Short Range and Long Range 

Airplanes 

For purposes of this AD, short range 

airplanes are those with an average flight 

time lower than 1.5 flight hours, and normal 

range airplanes are those with an average 

flight time equal to or higher than 1.5 flight 

hours. 

(k) Exception to Service Information 

Where the Accomplishment Instructions of 

Airbus Mandatory Service Bulletin A300–57– 

6037, Revision 04, dated February 24, 2011, 

specify contacting Airbus for an approved 

repair: Before further flight, contact either the 

Manager, International Branch, ANM–116, 

Transport Airplane Directorate, FAA, or the 

European Aviation Safety Agency (EASA) (or 

its delegated agent), for instructions and do 

those instructions. 

(l) Credit for Previous Actions 

This paragraph provides credit for actions 

required by paragraphs (g) and (h) of this AD, 

if those actions were performed before the 

effective date of this AD using any of the 

service bulletins specified in paragraphs 

(l)(1) through (l)(4) of this AD. 

(1) Airbus Mandatory Service Bulletin 

A300–57–6037, dated August 1, 1994, which 

was incorporated by reference in AD 2000– 

12–11, Amendment 39–11789 (65 FR 37853, 

June 19, 2000). 

(2) Airbus Mandatory Service Bulletin 

A300–57–6037, Revision 01, dated August 

31, 1995, which was incorporated by 

reference in AD 2000–12–11, Amendment 

39–11789 (65 FR 37853, June 19, 2000). 

(3) Airbus Mandatory Service Bulletin 

A300–57–6037, Revision 02, dated January 9, 

2001, which is not incorporated by reference 

in this AD. 

(4) Airbus Mandatory Service Bulletin 

A300–57–6037, Revision 03, dated January 

11, 2002, which is not incorporated by 

reference in this AD. 

(m) 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: 

Dan Rodina, Aerospace Engineer, 

International Branch, ANM–116, Transport 

Airplane Directorate, FAA, 1601 Lind 

Avenue SW., Renton, WA 98057–3356; 

phone: (425) 227–2125; 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. 

(3) AMOCs Approved Previously: AMOCs 

approved previously in accordance with AD 

2000–12–11, Amendment 39–11789 (65 FR 

37853, June 19, 2000), are approved as 

AMOCs for the corresponding provisions of 

this AD. 

(n) Related Information 

(1) Refer to Mandatory Continuing 

Airworthiness Information EASA 

Airworthiness Directive 2012–0138, dated 

July 26, 2012, for related information. You 

may examine the MCAI in the AD docket on 

the Internet at http://www.regulations.gov/

#!documentDetail;D=FAA-2013-0539-0002. 

(2) Service information identified in this 

AD that is not incorporated by reference may 

be obtained at the addresses specified in 

paragraphs (o)(4) and (o)(5) of this AD. 

(o) 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. 

(3) The following service information was 

approved for IBR on December 2, 2013. 

(i) Airbus Mandatory Service Bulletin 

A300–57–6037, Revision 04, dated February 

24, 2011. 

(ii) Reserved. 

(4) For service information identified in 

this AD, contact Airbus SAS—EAW 

(Airworthiness Office), 1 Rond Point Maurice 

Bellonte, 31707 Blagnac Cedex, France; 

telephone +33 5 61 93 36 96; fax +33 5 61 


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93 44 51; email account.airworth-eas@

airbus.com; Internet http://www.airbus.com. 

(5) You may view this 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. 

(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 

September 18, 2013. 

Ross Landes, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2013–25295 Filed 10–25–13; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2013–0465; Directorate 

Identifier 2012–NM–085–AD; Amendment 

39–17617; AD 2013–20–11] 

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 

oxygen generators installed on a certain 

batch of passenger emergency oxygen 

container assemblies might become 

detached by extreme pulling of the mask 

tube at the end of the oxygen supply 

causing a high temperature oxygen 

generator and mask to fall down. This 

AD requires modifying the passenger 

emergency oxygen container assembly. 

We are issuing this AD to prevent a high 

temperature oxygen generator and mask 

from falling down and possibly 

resulting in an ignition source in the 

passenger compartment, injury to 

passengers, and reduced availability of 

supplemental oxygen. 

DATES: This AD becomes effective 

December 2, 2013. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in this AD 

as of December 2, 2013. 

ADDRESSES: You may examine the AD 

on the Internet at http://

www.regulations.gov/

#!docketDetail;D=FAA-2013-0465; 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 3, 2013 (78 FR 40074). 

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 2012–0055, 

dated April 3, 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: 

It has been determined that oxygen 

generators, installed on a specific batch of 

Type 1 (22 minute) passenger emergency 

oxygen container assemblies, may become 

detached by extreme pulling of the mask tube 

at the end of oxygen supply. Investigations 

revealed that such detachment can be caused 

by the increase in temperature towards the 

end of the generator operation, which may 

weaken the plastic housing in the attachment 

area of the bracket. 

This condition, if not corrected, could 

make the rivets slip through the plastic 

housing, causing a ‘hot’ oxygen generator and 

mask to fall down, possibly resulting in 

injury to passengers. 

For the reasons described above, this 

[EASA] AD requires modification of the 

affected oxygen container assemblies. This 

[EASA] AD also prohibits the installation of 

the affected (unmodified) containers on any 

aeroplane as replacement parts. 

The modification consists of adding a 

reinforcement plate at the rear outside 

of the container and adding two washers 

to the rivets at the inside of the 

container to prevent the generator from 

detaching. You may examine the MCAI 

in the AD docket on the Internet at 

http://www.regulations.gov/

#!documentDetail;D=FAA-2013-0465- 

0002. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. We 

received no comments on the NPRM (78 

FR 40074, July 3, 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 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 

40074, July 3, 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 40074, 

July 3, 2013). 

Costs of Compliance 

We estimate that this AD affects 4 

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 

Modification ..................................................... 2 work-hours × $85 per hour = $170 ............. $0 $170 $680 


wreier-aviles on DSK5TPTVN1PROD with RULES