44660 Federal Register / Vol. 79, No. 148 / Friday, August 1, 2014 / Rules and Regulations 

attitude, or high-speed conditions, are 

acceptable as long as they allow at least 

45 degrees of roll capability. 

Issued in Renton, Washington, on July 11, 

2014. 

Michael Kaszycki, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2014–18176 Filed 7–31–14; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2014–0486; Directorate 

Identifier 2014–NM–126–AD; Amendment 

39–17918; AD 2014–15–16] 

RIN 2120–AA64 

Airworthiness Directives; Airbus 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule; request for 

comments. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for certain 

Airbus Model A319–111, –112, –115, 

–132, and –133 airplanes; Model A320– 

214, –232, and –233 airplanes; and 

Model A321–211, –231, and –232 

airplanes. This AD requires a detailed 

inspection for missing fasteners on the 

frame between certain stringers; for 

certain airplanes, a rototest inspection 

of the fastener holes for cracking; and 

corrective actions if necessary. This AD 

was prompted by a report that when the 

cabin lining was removed during a 

cabin conversion it was discovered that 

fasteners were missing on the frame. We 

are issuing this AD to detect and correct 

missing fasteners which, if not 

corrected, could affect the structural 

integrity of the airframe and could result 

in rapid decompression. 

DATES: This AD becomes effective 

August 18, 2014. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in this AD 

as of August 18, 2014. 

We must receive comments on this 

AD by September 15, 2014. 

ADDRESSES: You may send comments, 

using the procedures found in 14 CFR 

11.43 and 11.45, by any of the following 

methods: 

• Federal eRulemaking Portal: Go to 

http://www.regulations.gov. Follow the 

instructions for submitting comments. 

• Fax: 202–493–2251. 

• Mail: U.S. Department of 

Transportation, Docket Operations, 

M–30, West Building Ground Floor, 

Room W12–140, 1200 New Jersey 

Avenue SE., Washington, DC 20590. 

• Hand Delivery: U.S. Department of 

Transportation, Docket Operations, 

M–30, West Building Ground Floor, 

Room W12–140, 1200 New Jersey 

Avenue SE., Washington, DC, between 9 

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

Friday, except Federal holidays. 

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 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 by searching for 

and locating Docket No. FAA–2014– 

0486; 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. Comments will be available in 

the AD docket shortly after receipt. 

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 

The European Aviation Safety Agency 

(EASA), which is the Technical Agent 

for the Member States of the European 

Community, has issued EASA 

Airworthiness Directive 2014–0146, 

dated June 11, 2014 (referred to after 

this as the Mandatory Continuing 

Airworthiness Information, or ‘‘the 

MCAI’’), to correct an unsafe condition 

for certain Airbus Model A319–111, 

–112, –115, –132, and –133 airplanes; 

Model A320–214, –232, and –233 

airplanes; and Model A321–211, –231, 

and –232 airplanes. The MCAI states: 

During cabin conversion of an A320 

aeroplane, after removal of the cabin lining, 

an area was discovered where fasteners were 

missing at frame (FR) 24 between stringer 

(STR) 17 and STR18. Investigation results 

revealed that the available data concerning 

installation on the final assembly line was 

insufficient to pinpoint the exact MSN 

[manufacturer serial number] on which the 

affected assemblies were installed. However, 

a ‘group’ of MSN suspected to be affected 

was identified. Results of the static analysis 

performed show that the structure is still able 

to sustain Limit and Ultimate loads. 

However, the fatigue aspects indicate that 

long-term effects can be expected. 

This condition, if not corrected, could 

affect the structural integrity of the airframe. 

Prompted by these findings, Airbus issued 

Alert Operators Transmission (AOT) 

A53N006–14 and Service Bulletin (SB) 

A320–53–1285 to provide inspection 

instructions. 

For the reasons described above, this 

[EASA] AD requires a one-time detailed 

inspection (DET) [for missing fasteners] of 

the aeroplane structure at FR24 and, 

depending on findings, [a rototest inspection 

of the fastener holes for cracking and] 

accomplishment of applicable corrective 

actions. 

Corrective actions include repairing 

cracking and installing fasteners. 

You may examine the MCAI on the 

Internet at http://www.regulations.gov 

by searching for and locating Docket No. 

FAA–2014–0486. 

Relevant Service Information 

Airbus has issued the following 

service information. The actions 

described in this service information are 

intended to correct the unsafe condition 

identified in the MCAI. 

• Alert Operators Transmission 

A53N006–14, dated May 13, 2014. 

• Service Bulletin A320–53–1285, dated 

January 29, 2014. 

FAA’s Determination and Requirements 

of This AD 

This product has been approved by 

the aviation authority of another 

country, and is approved for operation 

in the United States. Pursuant to our 

bilateral agreement with the State of 

Design Authority, we have been notified 

of the unsafe condition described in the 

MCAI and service information 

referenced above. We are issuing this 

AD because we evaluated all pertinent 

information and determined the unsafe 

condition exists and is likely to exist or 

develop on other products of these same 

type designs. 

‘‘Contacting the Manufacturer’’ 

Paragraph in This AD 

Since late 2006, we have included a 

standard paragraph titled ‘‘Airworthy 

Product’’ in all MCAI ADs in which the 


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Federal Register / Vol. 79, No. 148 / Friday, August 1, 2014 / Rules and Regulations 44661 

FAA develops an AD based on a foreign 

authority’s AD. 

The MCAI or referenced service 

information in an FAA AD often directs 

the owner/operator to contact the 

manufacturer for corrective actions, 

such as a repair. Briefly, the Airworthy 

Product paragraph allowed owners/

operators to use corrective actions 

provided by the manufacturer if those 

actions were FAA-approved. In 

addition, the paragraph stated that any 

actions approved by the State of Design 

Authority (or its delegated agent) are 

considered to be FAA-approved. 

In an NPRM having Directorate 

Identifier 2012–NM–101–AD (78 FR 

78285, December 26, 2013), we 

proposed to prevent the use of repairs 

that were not specifically developed to 

correct the unsafe condition, by 

requiring that the repair approval 

provided by the State of Design 

Authority or its delegated agent 

specifically refer to the FAA AD. This 

change was intended to clarify the 

method of compliance and to provide 

operators with better visibility of repairs 

that are specifically developed and 

approved to correct the unsafe 

condition. In addition, we proposed to 

change the phrase ‘‘its delegated agent’’ 

to include a design approval holder 

(DAH) with State of Design Authority 

design organization approval (DOA), as 

applicable, to refer to a DAH authorized 

to approve required repairs for the 

proposed AD. 

One commenter to the NPRM having 

Directorate Identifier 2012–NM–101–AD 

(78 FR 78285, December 26, 2013), 

stated the following: ‘‘The proposed 

wording, being specific to repairs, 

eliminates the interpretation that Airbus 

messages are acceptable for approving 

minor deviations (corrective actions) 

needed during accomplishment of an 

AD mandated Airbus service bulletin.’’ 

This comment has made the FAA 

aware that some operators have 

misunderstood or misinterpreted the 

Airworthy Product paragraph to allow 

the owner/operator to use messages 

provided by the manufacturer as 

approval of deviations during the 

accomplishment of an AD-mandated 

action. The Airworthy Product 

paragraph does not approve messages or 

other information provided by the 

manufacturer for deviations to the 

requirements of the AD-mandated 

actions. The Airworthy Product 

paragraph only addresses the 

requirement to contact the manufacturer 

for corrective actions for the identified 

unsafe condition and does not cover 

deviations from other AD requirements. 

However, deviations to AD-required 

actions are addressed in 14 CFR 39.17, 

and anyone may request the approval 

for an alternative method of compliance 

to the AD-required actions using the 

procedures found in 14 CFR 39.19. 

To address this misunderstanding and 

misinterpretation of the Airworthy 

Product paragraph, we have changed 

that paragraph and retitled it 

‘‘Contacting the Manufacturer.’’ This 

paragraph now clarifies that for any 

requirement in this AD to obtain 

corrective actions from a manufacturer, 

the action must be accomplished using 

a method approved by the FAA, the 

European Aviation Safety Agency 

(EASA), or Airbus’s EASA DOA. 

The Contacting the Manufacturer 

paragraph also clarifies that, if approved 

by the DOA, the approval must include 

the DOA-authorized signature. The DOA 

signature indicates that the data and 

information contained in the document 

are EASA-approved, which is also FAAapproved. Messages and other 

information provided by the 

manufacturer that do not contain the 

DOA-authorized signature approval are 

not EASA-approved, unless EASA 

directly approves the manufacturer’s 

message or other information. 

This clarification does not remove 

flexibility previously afforded by the 

Airworthy Product paragraph. 

Consistent with long-standing FAA 

policy, such flexibility was never 

intended for required actions. This is 

also consistent with the 

recommendation of the Airworthiness 

Directive Implementation Aviation 

Rulemaking Committee to increase 

flexibility in complying with ADs by 

identifying those actions in 

manufacturers’ service instructions that 

are ‘‘Required for Compliance’’ with 

ADs. We continue to work with 

manufacturers to implement this 

recommendation. But once we 

determine that an action is required, any 

deviation from the requirement must be 

approved as an alternative method of 

compliance. 

FAA’s Determination of the Effective 

Date 

An unsafe condition exists that 

requires the immediate adoption of this 

AD. The FAA has found that the risk to 

the flying public justifies waiving notice 

and comment prior to adoption of this 

rule because missing fasteners on the 

frame may affect the structural integrity 

of the circumferential joint, which 

might result in rapid decompression. 

Therefore, we determined that notice 

and opportunity for public comment 

before issuing this AD are impracticable 

and that good cause exists for making 

this amendment effective in fewer than 

30 days. 

Comments Invited 

This AD is a final rule that involves 

requirements affecting flight safety, and 

we did not precede it by notice and 

opportunity for public comment. We 

invite you to send any written relevant 

data, views, or arguments about this AD. 

Send your comments to an address 

listed under the ADDRESSES section. 

Include ‘‘Docket No. FAA–20**–*****; 

Directorate Identifier 2014–NM–126– 

AD’’ at the beginning of your comments. 

We specifically invite comments on the 

overall regulatory, economic, 

environmental, and energy aspects of 

this AD. We will consider all comments 

received by the closing date and may 

amend this AD based on those 

comments. 

We will post all comments we 

receive, without change, to http://

www.regulations.gov, including any 

personal information you provide. We 

will also post a report summarizing each 

substantive verbal contact we receive 

about this AD. 

Costs of Compliance 

We estimate that this AD affects 7 

airplanes of U.S. registry. 

We also estimate that it will take 

about 1 work-hour per product to 

comply with the basic requirements of 

this AD. The average labor rate is $85 

per work-hour. Based on these figures, 

we estimate the cost of this AD on U.S. 

operators to be $595, or $85 per product. 

In addition, we estimate that any 

necessary follow-on actions will take 

about 39 work-hours and require parts 

costing $0, for a cost of $3,315 per 

product. We have no way of 

determining the number of aircraft that 

might need these actions. 

We have received no definitive data 

that would enable us to provide cost 

estimates for the on-condition repair 

specified in this AD. 

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. 

Paperwork Reduction Act 

A federal agency may not conduct or 

sponsor, and a person is not required to 

respond to, nor shall a person be subject 

to penalty for failure to comply with a 

collection of information subject to the 

requirements of the Paperwork 

Reduction Act unless that collection of 

information displays a current valid 

OMB control number. The control 

number for the collection of information 


emcdonald on DSK67QTVN1PROD with RULES
44662 Federal Register / Vol. 79, No. 148 / Friday, August 1, 2014 / Rules and Regulations 

required by this AD is 2120–0056. The 

paperwork cost associated with this AD 

has been detailed in the Costs of 

Compliance section of this document 

and includes time for reviewing 

instructions, as well as completing and 

reviewing the collection of information. 

Therefore, all reporting associated with 

this AD is mandatory. Comments 

concerning the accuracy of this burden 

and suggestions for reducing the burden 

should be directed to the FAA at 800 

Independence Ave. SW., Washington, 

DC 20591, ATTN: Information 

Collection Clearance Officer, AES–200. 

Authority for This Rulemaking 

Title 49 of the United States Code 

specifies the FAA’s authority to issue 

rules on aviation safety. Subtitle I, 

section 106, describes the authority of 

the FAA Administrator. ‘‘Subtitle VII: 

Aviation Programs,’’ describes in more 

detail the scope of the Agency’s 

authority. 

We are issuing this rulemaking under 

the authority described in ‘‘Subtitle VII, 

Part A, Subpart III, Section 44701: 

General requirements.’’ Under that 

section, Congress charges the FAA with 

promoting safe flight of civil aircraft in 

air commerce by prescribing regulations 

for practices, methods, and procedures 

the Administrator finds necessary for 

safety in air commerce. This regulation 

is within the scope of that authority 

because it addresses an unsafe condition 

that is likely to exist or develop on 

products identified in this rulemaking 

action. 

Regulatory Findings 

We determined that this AD will not 

have federalism implications under 

Executive Order 13132. This 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. 

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): 

2014–15–16 Airbus: Amendment 39–17918. 

Docket No. FAA–2014–0486; Directorate 

Identifier 2014–NM–126–AD. 

(a) Effective Date 

This AD becomes effective August 18, 

2014. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to the Airbus airplanes 

identified in paragraphs (c)(1), (c)(2), and 

(c)(3) of this AD, certificated in any category, 

manufacturer serial numbers (MSN) 5230 

through 5300 inclusive, except MSN 5255 

and 5295. 

(1) Model A319–111, –112, –115, –132, and 

–133 airplanes. 

(2) Model A320–214, –232, and –233 

airplanes. 

(3) Model A321–211, –231, and –232 

airplanes. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 53, Fuselage. 

(e) Reason 

This AD was prompted by a report that 

when the cabin lining was removed during 

a cabin conversion it was discovered that 

fasteners were missing on the frame. We are 

issuing this AD to detect and correct missing 

fasteners which, if not corrected, could affect 

the structural integrity of the airframe and 

could result in rapid decompression. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Detailed Inspection 

Within 60 flight cycles after the effective 

date of this AD: Do a detailed inspection to 

determine if any fasteners are missing on the 

structure at frame (FR) 24 between stringer 

(STR) 17 and STR 18 on the right side only, 

in accordance with the instructions in Airbus 

Alert Operators Transmission A53N006–14, 

dated May 13, 2014. 

(h) Rototest Inspection and Corrective 

Actions 

If, during the detailed inspection required 

by paragraph (g) of this AD, any fastener is 

found missing: Before the accumulation of 

3,300 flight cycles since the airplane’s first 

flight, or within 60 flight cycles after the 

effective date of this AD, whichever occurs 

later, do a rototest inspection of the fastener 

holes for cracking and do all applicable 

corrective actions, in accordance with the 

Accomplishment Instructions of Airbus 

Service Bulletin A320–53–1285, dated 

January 29, 2014, except as required by 

paragraph (i) of this AD. Do all applicable 

corrective actions before further flight. 

(i) Repair 

If any crack is found during any inspection 

required by paragraph (h) of this AD: 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 Airbus’s EASA 

Design Organization Approval (DOA). If 

approved by the DOA, the approval must 

include the DOA-authorized signature. 

(j) Reporting Requirement 

At the applicable time specified in 

paragraph (j)(1) or (j)(2) of this AD, report 

both positive and negative results of the 

inspections required by paragraphs (g) and 

(h) of this AD, as applicable, to Airbus, 

Customer Services Engineering, Emeric 

Mevel, Structure Engineer, Structure 

Engineering Support—SEES1, Customer 

Services; telephone +33(0)5 67–19 02 41; fax 

+33(0) 5 61 93 36 14; email emeric.mevel@

airbus.com. The report must include the 

information specified in Figure A–FRAAA of 

Airbus Service Bulletin A320–53–1285, 

dated January 29, 2014. 

(1) If the inspection was done on or after 

the effective date of this AD: Within 30 days 

after that inspection. 

(2) If the inspection was done before the 

effective date of this AD: Within 30 days after 

the effective date of this AD. 

(k) 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: 

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 


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Federal Register / Vol. 79, No. 148 / Friday, August 1, 2014 / Rules and Regulations 44663 

district office. The AMOC approval letter 

must specifically reference this AD. 

(2) Contacting the Manufacturer: For any 

requirement in this AD to obtain corrective 

actions from a manufacturer, the action must 

be accomplished using a method approved 

by the Manager, International Branch, ANM– 

116, Transport Airplane Directorate, FAA; or 

the European Aviation Safety Agency 

(EASA); or Airbus’s EASA Design 

Organization Approval (DOA). If approved by 

the DOA, the approval must include the 

DOA-authorized signature. 

(3) Reporting Requirements: A federal 

agency may not conduct or sponsor, and a 

person is not required to respond to, nor 

shall a person be subject to a penalty for 

failure to comply with a collection of 

information subject to the requirements of 

the Paperwork Reduction Act unless that 

collection of information displays a current 

valid OMB Control Number. The OMB 

Control Number for this information 

collection is 2120–0056. Public reporting for 

this collection of information is estimated to 

be approximately 5 minutes per response, 

including the time for reviewing instructions, 

completing and reviewing the collection of 

information. All responses to this collection 

of information are mandatory. Comments 

concerning the accuracy of this burden and 

suggestions for reducing the burden should 

be directed to the FAA at: 800 Independence 

Ave. SW., Washington, DC 20591, Attn: 

Information Collection Clearance Officer, 

AES–200. 

(l) Related Information 

Refer to Mandatory Continuing 

Airworthiness Information (MCAI) EASA 

Airworthiness Directive 2014–0146, dated 

June 11, 2014, for related information. You 

may examine the MCAI on the Internet at 

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

and locating Docket No. FAA–2014–0486. 

(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 this AD specifies otherwise. 

(i) Airbus Alert Operators Transmission 

A53N006–14, dated May 13, 2014. 

(ii) Airbus Service Bulletin A320–53–1285, 

dated January 29, 2014. 

(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.airworth-eas@

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

(4) 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. 

(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 July 12, 

2014. 

Michael Kaszycki, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2014–17782 Filed 7–31–14; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2014–0228; Directorate 

Identifier 2013–NM–216–AD; Amendment 

39–17911; AD 2014–15–09] 

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 A330–200 Freighter, 

A330–200 and –300, and A340–200, 

–300, –500, and –600 series airplanes. 

This AD was prompted by reassessment 

of an unsafe condition related to MZtype spoiler servo-controls (SSCs) that 

did not remain locked in the retracted 

position (hydraulic locking function) 

after manual depressurization of the 

corresponding hydraulic circuit. This 

reassessment resulted in the 

determination that performing repetitive 

operational tests of all SSC types is 

necessary. This AD requires repetitive 

operational tests of the hydraulic 

locking function on each SSC installed 

on the blue or yellow hydraulic circuits, 

and replacing any affected SSC with a 

serviceable SSC. We are issuing this AD 

to detect and correct loss of the 

hydraulic locking function during takeoff, which, in combination with one 

inoperative engine, could result in 

reduced controllability of the airplane. 

DATES: This AD becomes effective 

September 5, 2014. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in this AD 

as of September 5, 2014. 

ADDRESSES: You may examine the AD 

docket on the Internet at http://

www.regulations.gov/

#!docketDetail;D=FAA-2014-0228 or in 

person at the Docket 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. 

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. 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. 

FOR FURTHER INFORMATION CONTACT: 

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. 

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 all Airbus Model A330–200 

Freighter, A330–200 and –300, and 

A340–200, –300, –500, and –600 series 

airplanes. The NPRM published in the 

Federal Register on April 14, 2014 (79 

FR 20839). 

The European Aviation Safety Agency 

(EASA), which is the Technical Agent 

for the Member States of the European 

Community, has issued EASA 

Airworthiness Directive 2013–0251 

dated October 15, 2013; Correction 

dated October 16, 2013 (referred to after 

this as the Mandatory Continuing 

Airworthiness Information, or ‘‘the 

MCAI’’); to correct an unsafe condition 

for the specified products. The MCAI 

states: 

During post-flight maintenance checks 

accomplished on an A330 and on an A340 

airplane, it was identified that seven spoiler 

servo-controls MZ series had lost their 

hydraulic locking function. The results of the 

subsequent technical investigation 

accomplished in-shop by the part supplier 

confirmed the system failure was due to a 

sheared seal on the blocking valve, ensuring 

the blocking function of the spoiler. It is 

suspected that the seal damage may have 

occurred during accomplishment of a 

modification to fit a new design of 

maintenance cover on wing, required by 

EASA AD 2008–0160 [http://

ad.easa.europa.eu/blob/easa_ad_2008_

0160.pdf/AD_2008–0160], [which 

corresponds to FAA AD 2009–18–20, 

Amendment 39–16017 (74 FR 46313, 

September 9, 2009)]. 


emcdonald on DSK67QTVN1PROD with RULES