Federal Register / Vol. 79, No. 177 / Friday, September 12, 2014 / Rules and Regulations 54579 

(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 AD: 

2014–18–03 APEX Aircraft: Amendment 

39–17967; Docket No. FAA–2014–0647; 

Directorate Identifier 2014–CE–027–AD. 

(a) Effective Date 

This airworthiness directive (AD) becomes 

effective October 17, 2014. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to APEX Aircraft Models 

R 3000/160 airplanes, all serial numbers, 

certificated in any category. 

(d) Subject 

Air Transport Association of America 

(ATA) Code 73: Engine Fuel & Control. 

(e) Reason 

This AD was prompted by mandatory 

continuing airworthiness information (MCAI) 

issued by the aviation authority of another 

country to identify and correct an unsafe 

condition on an aviation product. The MCAI 

describes the unsafe condition as paint 

adherence defects inside the engine air intake 

box leading to small pieces of paint from the 

engine air intake box blocking the engine 

carburetor. We are issuing this AD to detect 

and correct paint adherence defects inside 

the engine air intake box leading to small 

pieces of paint from the engine air intake box 

blocking the engine carburetor. This 

condition, if not detected and corrected, 

could lead to an engine failure, possibly 

resulting in loss of control. 

(f) Actions and Compliance 

Unless already done, do the following 

actions, as specified in paragraphs (f)(1) 

through (f)(4) of this AD: 

(1) Within 110 hours time-in-service (TIS) 

after October 17, 2014 (the effective date of 

this AD) and repetitively thereafter at 

intervals not to exceed 110 hours TIS, 

accomplish a visual and tactile inspection of 

the engine air intake box (including the 

deflection flap) and the engine air ducting 

(including the area located downstream of 

the filter) following the Accomplishment 

Instructions section of CEAPR Mandatory 

Service Bulletin Number 161R3, dated 

September 6, 2012. 

(2) If any paint damage such as bubbling, 

blistering, peeled off areas or paint 

detachment is found during any inspection 

required by paragraph (f)(1) of this AD, before 

further flight, replace each damaged part 

with an airworthy part following the 

Accomplishment Instructions section of 

CEAPR Mandatory Service Bulletin Number 

161R3, dated September 6, 2012. 

(3) Replacement of damaged parts on an 

airplane, as required by paragraph (f)(2) of 

this AD, does not constitute terminating 

action for the repetitive inspections required 

by paragraph (f)(1) of this AD for that 

airplane. 

(4) As of October 17, 2014 (the effective 

date of this AD), do not install on any 

airplane a painted engine air intake box or 

repaired engine air ducting. 

(g) Other FAA AD Provisions 

The following provisions also apply to this 

AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, Standards Office, 

FAA, has the authority to approve AMOCs 

for this AD, if requested using the procedures 

found in 14 CFR 39.19. Send information to 

ATTN: Sarjapur Nagarajan, Aerospace 

Engineer, FAA, Small Airplane Directorate, 

901 Locust, Room 301, Kansas City, Missouri 

64106; telephone: (816) 329–4145; fax: (816) 

329–4090; email: sarjapur.nagarajan@

faa.gov. Before using any approved AMOC on 

any airplane to which the AMOC applies, 

notify your appropriate principal inspector 

(PI) in the FAA Flight Standards District 

Office (FSDO), or lacking a PI, your local 

FSDO. 

(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. 

(h) Related Information 

Refer to MCAI European Aviation Safety 

Agency (EASA) AD No. 2014–0155, dated 

July 2, 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–2014–0647. 

(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) CEAPR Mandatory Service Bulletin 

Number 161R3, dated September 6, 2012. 

Note 1 to paragraph (i)(2)(i) of this AD: 

The service bulletin contains French to 

English translation. EASA used the English 

translation in referencing the document from 

CEAPR. For enforceability purposes, we will 

cite references to the CEAPR service 

information as it appears on the document. 

(ii) Reserved. 

(3) For CEAPR service information 

identified in this AD, contact CEAPR, Bureau 

de Navigabilite ́, 1 route de Troyes, 21121 

DAROIS–France, telephone: (33) 380 35 25 

22; fax: (33) 380 35 25 25; email: www.info@

ceapr.com; internet: http://ceapr.com/. 

(4) You may view this service information 

at the FAA, Small Airplane Directorate, 901 

Locust, Kansas City, Missouri 64106. For 

information on the availability of this 

material at the FAA, call (816) 329–4148. 

(5) You may view this service information 

that is incorporated by reference at the 

National Archives and Records 

Administration (NARA). For information on 

the availability of this material at NARA, call 

202–741–6030, or go to: http://

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

Issued in Kansas City, Missouri, on August 

29, 2014. 

Earl Lawrence, 

Manager, Small Airplane Directorate, Aircraft 

Certification Service. 

[FR Doc. 2014–21270 Filed 9–11–14; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2013–0088; Directorate 

Identifier 2011–NM–233–AD; Amendment 

39–17703; AD 2013–25–07] 

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) 2007–18– 

09 for all Airbus Model A318, A319, 

A320, and A321 series airplanes. AD 

2007–18–09 required repetitive 

inspections of the upper support of the 

nose landing gear (NLG), and related 

investigative and corrective actions if 

necessary; and also provided an 

optional terminating action for the 

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54580 Federal Register / Vol. 79, No. 177 / Friday, September 12, 2014 / Rules and Regulations 

repetitive inspections. This new AD 

adds installation of a new enhanced 

manufacturing and maintainability 

(EMM) braking and steering control unit 

(BSCU) standard, and adds airplanes to 

the applicability. This AD was 

prompted by a determination that 

previously allowed terminating actions 

no longer address the unsafe condition 

and that a new terminating action is 

necessary. We are issuing this AD to 

prevent landings with the NLG turned 

90 degrees from centerline, which could 

result in reduced controllability of the 

airplane. 

DATES: This AD becomes effective 

October 17, 2014. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in this AD 

as of October 17, 2014. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain other publication listed in 

this AD as of October 11, 2007 (72 FR 

51164, September 6, 2007). 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain other publication listed in 

this AD as of November 30, 2005 (70 FR 

70715, November 23, 2005). 

ADDRESSES: You may examine the AD 

docket on the Internet at http://

www.regulations.gov/#!docket

Detail;D=FAA-2013-0088; 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 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: 

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 supersede AD 2007–18–09, 

Amendment 39–15189 (72 FR 51164, 

September 6, 2007), which superseded 

AD 2005–24–06, Amendment 39–14386 

(70 FR 70715, November 23, 2005). AD 

2007–18–09 applied to all Airbus Model 

A318, A319, A320, and A321 series 

airplanes. The NPRM published in the 

Federal Register on February 8, 2013 

(78 FR 9341). The NPRM was prompted 

by a determination that previously 

allowed terminating actions no longer 

address the identified unsafe condition 

and that a new terminating action is 

necessary. The NPRM proposed to 

continue to require repetitive 

inspections of the upper support of the 

NLG, and related investigative and 

corrective actions if necessary; and also 

provided a new optional terminating 

action for the repetitive inspections. The 

NPRM also proposed to install a new 

EMM BSCU standard, and add airplanes 

to the applicability. We are issuing this 

AD to prevent landings with the NLG 

turned 90 degrees from centerline, 

which could result in reduced 

controllability of the airplane. 

The European Aviation Safety Agency 

(EASA), which is the Technical Agent 

for the Member States of the European 

Community, has issued EASA 

Airworthiness Directive 2011–0201, 

dated October 13, 2011 (referred to after 

this as the Mandatory Continuing 

Airworthiness Information, or ‘‘the 

MCAI’’), to correct an unsafe condition 

for all Airbus Model A318, A319, A320, 

and A321 series airplanes. The MCAI 

states: 

In 2005, an A320 aeroplane experienced a 

landing with the Nose Landing Gear (NLG) 

wheels rotated at 90 degrees to the aeroplane 

centreline. 

Investigation showed that the upper 

support of the NLG shock absorber was 

damaged and the anti-rotation lugs were 

ruptured. This caused the nose wheels to lose 

their centred position reference. The affected 

Braking and Steering Control Unit (BSCU) 

had logged a steering system fault because 

hydraulic power was not available at the time 

of steering system checks, therefore the BSCU 

was not able to proceed with the re-centring 

of the wheels. Failure to centre the NLG 

wheels correctly may result in a failure of the 

NLG to retract. 

To prevent further landing incidents with 

NLG wheels rotated at 90 degrees, [Direction 

Ge ́ne ́rale de l’Aviation Civile] DGAC France 

issued AD F–2005–191 [(http://

ad.easa.europa.eu/blob/easa_ad_2005_6411_

F20051910tb_superseded.pdf/AD_F–2005– 

191_1) which corresponds to FAA AD 2005– 

24–06, Amendment 39–14386 (70 FR 70715, 

November 23, 2005)] to require the 

implementation of an operational procedure 

and the accomplishment of certain 

maintenance actions. 

EASA AD 2006–0174, [(http://

ad.easa.europa.eu/blob/easa_ad_2006_0174_

superseded.pdf/AD_2006–0174_2) which 

corresponds to FAA AD 2007–18–09, 

Amendment 39–15189 (72 FR 51164, 

September 6, 2007)] which superseded AD 

F–2005–191, was issued to extend the 

applicability and to introduce repetitive 

boroscope inspections of the NLG upper 

support lugs and cylinder lugs which have 

been driven by EMM BSCU L4.1 (Part 

Number (P/N) E21327001) or L4.5 (P/N 

E21327003) and, corrective actions, 

depending on findings. 

Since that [EASA] AD was issued, Airbus 

has demonstrated the acceptability of 

installing EMM BSCU L4.9B (P/N E21327006 

or P/N E21327106) or conventional BSCU std 

10 (P/N C202163392E34) or conventional 

BSCU std 10.1 (P/N C202163392E35) as 

terminating action for the actions required by 

EASA AD 2006–0174, for aeroplanes fitted 

with twin wheel Main Landing Gear (MLG) 

units. 

For the reasons described above, this 

[EASA] AD retains some of the requirements 

of EASA AD 2006–0174, which is 

superseded, extends the applicability to all 

A318, A319, A320 and A321 aeroplanes, 

requires the installation of BSCU L4.9B, or 

BSCU std 10, or BSCU std 10.1 for in service 

aeroplanes fitted with twin wheel MLG, 

which constitutes terminating action for the 

repetitive inspections and checks required by 

this [EASA] AD. 

Installation of a NLG with new upper 

support anti-rotation lugs and new cylinders 

lugs, or installation of a NLG for which it can 

be demonstrated that it was never driven by 

EMM BSCU L4.1 or L4.5, is no longer 

considered as terminating action for the 

requirements of this [EASA] AD. 

The unsafe condition is the NLG turning 

90 degrees from centerline, which could 

result in reduced controllability of the 

airplane. You may examine the MCAI in 

the AD docket on the Internet at http:// 

www.regulations.gov/#!document

Detail;D=FAA-2013-0088-0002. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. We 

have considered the comments received. 

Support for the NPRM (78 FR 9341, 

February 8, 2013) 

United Airlines (UAL) stated that it 

concurs with the FAA’s assertion that 

terminating action should consist of 

BSCU standard L4.9B, standard 10, or 

standard 10.1, rather than standard L4.1 

or L4.5. 

Statement of Compliance With the 

NPRM (78 FR 9341, February 8, 2013) 

UAL stated that it is currently in the 

process of upgrading its BSCU to the 

enhanced EMM version specified in the 

NPRM (78 FR 9341, February 8, 2013) 

and is 81 percent complete. 

Request for Alternative Actions 

UAL stated that the NPRM (78 FR 

9341, February 8, 2013) mandates 

accomplishment of the BSCU 

replacement within 6 months after the 

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Federal Register / Vol. 79, No. 177 / Friday, September 12, 2014 / Rules and Regulations 54581 

effective date of the AD, and that it is 

concerned the vendor may not be able 

to support this relatively short deadline 

with sufficient numbers of enhanced 

BSCUs. UAL asserted that a more 

feasible solution with an acceptable 

level of safety would be: 

• Continue repetitive inspections of 

the upper support of the nose landing 

gear (NLG) until replacement with the 

EMM BSCU. 

• Continue repetitive inspections of 

the NLG for airplanes on which the 

terminating action per AD 2007–18–09, 

Amendment 39–15189 (72 FR 51164, 

September 6, 2007)—standard L4.1, 

L4.5, or L5–2 was done previously. 

• Upgrade to the standard L4.9B, 

standard 10, or standard 10.1, could 

then be accomplished on attrition, as 

units are available from the BSCU 

manufacturer. 

We disagree with the commenter’s 

request. The compliance time for 

modification of EMM BSCU standard 

L4.9B was determined after conducting 

a risk assessment and determining the 

effect of associated risk on the 

worldwide fleet. We have determined 

that for twin wheel MLG, the repetitive 

inspection of the NLG upper support 

lugs and missing cylinder cannot be 

relied upon indefinitely until 

replacement with EMM BSCU standard 

L4.9B or applicable alternatives 

specified in paragraph (w) of this AD by 

attrition. Modification is not required by 

paragraph (v) of this AD for airplanes 

installed with bogie MLG. Only 

airplanes fitted with twin wheel MLG 

must do the modification within 6 

months. 

The compliance time was also 

established taking into consideration 

availability of parts. Operators have 

multiple options to install EMM BSCU 

standards in accordance with paragraph 

(w) of this AD. However, according to 

the provisions of paragraph (bb)(1) of 

this AD, we might approve requests to 

adjust the compliance time or allow 

alternative actions if the requests 

include substantiation that the new 

compliance time or alternative actions 

would provide an acceptable level of 

safety. We have not changed this final 

rule in this regard. 

‘‘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 

FAA develops an AD based on a foreign 

authority’s AD. 

We have become 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 ADmandated 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 the 

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 actions must be 

accomplished using a method approved 

by the FAA, the EASA, or Airbus’s 

EASA Design Organization Approval 

(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. 

We also have decided not to include 

a generic reference to either the 

‘‘delegated agent’’ or ‘‘design approval 

holder (DAH) with State of Design 

Authority design organization 

approval,’’ but instead we have 

provided the specific delegation 

approval granted by the State of Design 

Authority for the DAH throughout this 

AD. 

Additional Changes Made to This Final 

Rule 

We have removed Note 1 to paragraph 

(i) of the proposed AD (78 FR 9341, 

February 8, 2013) and included that 

information in paragraph (i) of this AD. 

This change does not affect the intent of 

paragraph (i) of this AD. 

We have also revised paragraph (m) of 

this AD to remove a reference to Chapter 

32 of the Airbus A318/A319/A320/A321 

Aircraft Maintenance Manual (AMM). 

As of the effective date of this AD, 

operators must contact the Manager, 

International Branch, ANM–116, 

Transport Airplane Directorate, FAA; or 

EASA; or Airbus’s EASA DOA; as 

specified in paragraph (bb)(1) of this AD 

for approval to use this document. We 

also added a new Note 1 to paragraph 

(m) of this AD, which specifies that 

guidance for doing the installation 

required by paragraph (m) of this AD 

may be found in Chapter 32 of the 

Airbus A318/A319/A320/A321 AMM. 

In addition, we have clarified 

paragraph (o) of this AD to indicate 

which part numbers correspond to 

which EMM units. 

We removed Note 2 to paragraph (p) 

of the proposed AD (78 FR 9341, 

February 8, 2013) and included that 

information in new paragraph (aa)(3) of 

this AD. We have redesignated 

subsequent paragraphs accordingly. 

This change does not affect the intent of 

paragraph (p) of this AD. 

We removed Note 3 to paragraph (r) 

of the proposed AD (78 FR 9341, 

February 8, 2013) and included that 

information in paragraph (r) of this AD. 

This change does not affect the intent of 

paragraph (r) of this AD. 

Also, we revised paragraph (x) of the 

proposed AD (78 FR 9341, February 8, 

2013) to indicate that accomplishing a 

modification specified in paragraph (w) 

of this AD is also a terminating action 

for the inspections required by 

paragraph (t) of this AD. 

Paragraph (y) of the proposed AD (78 

FR 9341, February 8, 2013) included a 

typographical error in the exception 

phrase. We have revised this AD to 

clarify the exception by specifying 

‘‘Except for the prohibition specified in 

paragraph (z) of this AD. . . .’’ 

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54582 Federal Register / Vol. 79, No. 177 / Friday, September 12, 2014 / Rules and Regulations 

Conclusion 

We reviewed the available data, 

including the comments 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 (78 FR 9341, 

February 8, 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 9341, 

February 8, 2013). 

We also determined that these 

changes will not increase the economic 

burden on any operator or increase the 

scope of this AD. 

Costs of Compliance 

We estimate that this AD affects about 

755 products of U.S. registry. 

The actions that are retained from AD 

2007–18–09, Amendment 39–15189 (72 

FR 51164, September 6, 2007), take 

about 3 work-hours per product, at an 

average labor rate of $85 per work hour. 

Based on these figures, the estimated 

cost of the actions that were required by 

AD 2007–18–09 is $255 per product. 

We estimate that it will take 35 workhours per product to comply with the 

new basic requirements of this AD. The 

average labor rate is $85 per work-hour. 

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 $2,246,125, or $2,975 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 might 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. 

Examining the AD Docket 

You may examine the AD docket on 

the Internet at http://

www.regulations.gov/#!docketDetail;

D=FAA-2013-0088; 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 

removing Airworthiness Directive (AD) 

2007–18–09, Amendment 39–15189 (72 

FR 51164, September 6, 2007), and 

adding the following new AD: 

2013–25–07 Airbus: Amendment 39–17703. 

Docket No. FAA–2013–0088; Directorate 

Identifier 2011–NM–233–AD. 

(a) Effective Date 

This airworthiness directive (AD) becomes 

effective October 17, 2014. 

(b) Affected ADs 

This AD replaces AD 2007–18–09, 

Amendment 39–15189 (72 FR 51164, 

September 6, 2007). 

(c) Applicability 

This AD applies to the Airbus airplanes 

listed in paragraphs (c)(1), (c)(2), (c)(3), and 

(c)(4) of this AD, certificated in any category, 

all serial numbers. 

(1) Model A318–111, –112, –121, and –122 

airplanes. 

(2) Model A319–111, –112, –113, –114, 

–115, –131, –132, and –133 airplanes. 

(3) Model A320–111, –211, –212, –214, 

–231, –232, and –233 airplanes. 

(4) Model A321–111, –112, –131, –211, 

–212, –213, –231, and –232 airplanes. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 32, Landing gear. 

(e) Reason 

This AD was prompted by a report of an 

airplane landing with the nose landing gear 

(NLG) turned 90 degrees from centerline, and 

from additional reports of upper support 

anti-rotation lugs of the NLG rupturing in 

service. We are issuing this AD to prevent 

landings with the NLG turned 90 degrees 

from centerline, which could result in 

reduced controllability of the airplane. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Retained Records Review 

This paragraph restates the requirements of 

paragraph (f) of AD 2007–18–09, Amendment 

39–15189 (72 FR 51164, September 6, 2007). 

Within 5 days after November 30, 2005 (the 

effective date of AD 2005–24–06, 

Amendment 39–14386 (70 FR 70715, 

November 23, 2005)), perform a records 

review to determine whether the airplane is 

equipped with or has ever been equipped 

with an enhanced manufacturing and 

maintainability (EMM) braking and steering 

control unit (BSCU) having part number (P/ 

N) E21327001 (standard L4.1, installed by 

Airbus Modification 26965 or Airbus Service 

Bulletin A320–32–1912) or P/N E21327003 

(standard L4.5, installed by Airbus 

Modification 33376 or Airbus Service 

Bulletin A320–32–1261). Airbus Service 

Bulletin A320–32–1310, dated February 8, 

2006, is one approved method for doing the 

records review. 

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Federal Register / Vol. 79, No. 177 / Friday, September 12, 2014 / Rules and Regulations 54583 

(h) Retained Statement of No Further Action 

Required After Records Review 

This paragraph restates a provision from 

paragraph (g) of AD 2007–18–09, 

Amendment 39–15189 (72 FR 51164, 

September 6, 2007). For airplanes on which 

a records review required by paragraph (g) of 

this AD conclusively determines that the 

airplane is not and never has been equipped 

with a BSCU P/N E21327001 or P/N 

E21327003, no further action is required by 

paragraphs (i), (j), (k), (l), and (m) of this AD. 

(i) Retained AFM Revision 

This paragraph restates the requirements of 

paragraph (h) of AD 2007–18–09, 

Amendment 39–15189 (72 FR 51164, 

September 6, 2007). For airplanes that are not 

specified in paragraph (h) of this AD and on 

which Airbus Modification 31152 has not 

been incorporated in production (i.e., 

applicable only to aircraft with steering 

powered by the green hydraulic system): 

Within 10 days after November 30, 2005 (the 

effective date of AD 2005–24–06, 

Amendment 39–14386 (70 FR 70715, 

November 23, 2005)), revise the Limitation 

Section of the Airbus A318/319/320/321 

AFM to include the following information. 

This may be done by inserting a copy of 

figure 1 to paragraph (i) of this AD into the 

AFM. Accomplishment of the actions 

required by paragraph (r) of this AD 

terminates the requirements of this 

paragraph, and the AFM limitation required 

by this paragraph must be removed. When a 

statement identical to that in figure 1 to 

paragraph (i) of this AD has been included 

in the general revisions of the AFM, the 

general revisions may be inserted into the 

AFM, and the copy of figure 1 to paragraph 

(i) of this AD or AD 2007–18–09, 

Amendment 39–15189 (72 FR 51164, 

September 6, 2007), may be removed from 

the AFM. 

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54584 Federal Register / Vol. 79, No. 177 / Friday, September 12, 2014 / Rules and Regulations 

BILLING CODE 4910–13–C 

(j) Retained Inspection Thresholds 

This paragraph restates the requirements of 

paragraph (i) of AD 2007–18–09, Amendment 

39–15189 (72 FR 51164, September 6, 2007), 

with specific delegation approval language. 

For airplanes that are not specified in 

paragraph (h) of this AD: At the earlier of the 

times specified in paragraphs (j)(1) and (j)(2) 

of this AD, do a special detailed inspection 

(boroscopic) for broken or cracked NLG 

upper support lugs and missing cylinder 

lugs, and do all applicable related 

investigative/corrective actions before further 

flight. Do all actions in accordance with 

Airbus Technical Note 957.1901/05, dated 

October 18, 2005; or the Accomplishment 

Instructions of Airbus Service Bulletin A320– 

32–1310, dated February 8, 2006. After 

October 11, 2007 (the effective date of AD 

2007–18–09), only Airbus Service Bulletin 

A320–32–1310, dated February 8, 2006, may 

be used. Where Airbus Service Bulletin 

A320–32–1310, dated February 8, 2006, 


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Figure 1 to Paragraph (i) of this AD -Retained AFM Revision 

The ECAM message, in case of a nose wheel steering failure, will be 

worded as follows: 

-"WHEEL N/W STRG FAULT" for aircraft with the FWC E3 and 

subsequent standards 

-"WHEEL N. W. STEER FAULT" for aircraft with the FWC E2 

Standard. 

• Ifthe L/G SHOCK ABSORBER FAULT ECAM caution is 

triggered at any time in flight, and the WHEEL N/W STRG FAULT 

ECAM caution is triggered after the landing gear extension: 

When all landing gear doors are indicated closed on ECAM WHEEL 

page, reset the BSCU: 

- A/SKlD&N/W STRG---------------------- OFF THEN ON 

Ifthe WHEEL N/W STRG FAULT ECAM caution is no longer 

displayed, this indicates a successful nose wheel re-centering and 

steering recovery. 

- Rearm the AUTO BRAKE, if necessary. 

If the WHEEL N/W STRG FAULT ECAM caution remains 

displayed, this indicates that the nose wheel steering remains lost, 

and that the nose wheels are not centered. 

- During landing, delay nose wheel touchdown for as long as 

possible. 

-Refer to the ECAM STATUS. 

• Ifthe WHEEL N/W STRG FAULT ECAM caution appears, 

without the LIG SHOCK ABSORBER FAULT ECAM caution: 

-No specific crew action is requested by the WHEEL N/W STRG 

FAULT ECAM caution procedure. 

-Refer to the ECAM STATUS. 
Federal Register / Vol. 79, No. 177 / Friday, September 12, 2014 / Rules and Regulations 54585 

specifies that restoring the NLG is necessary 

in accordance with Airbus recommendations, 

this AD requires restoring the NLG in 

accordance with 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). Repeat the inspection 

thereafter at the applicable interval specified 

in paragraph (k) or (l) of this AD until the 

inspection required by paragraph (t) of this 

AD is accomplished. 

(1) Within 100 flight cycles following an 

ECAM caution L/G SHOCK ABSORBER 

FAULT associated with at least one of the 

following CFDS messages specified in 

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

AD. As of the effective date of this AD, for 

the conditions specified in paragraph (j)(1) of 

this AD, do the actions required by paragraph 

(r) of this AD. 

(i) N L/G EXT PROX SNSR 24GA TGT 

POS. 

(ii) N L/G EXT PROX SNSR 25GA TGT 

POS. 

(iii) N L/G SHOCK ABSORBER FAULT 

2526GM. 

(2) At the later of the times specified in 

paragraphs (j)(2)(i) and (j)(2)(ii) of this AD. 

(i) Within 20 months, 6,000 flight hours, or 

4,500 flight cycles since the date of issuance 

of the original French standard airworthiness 

certificate or the original French export 

certificate of airworthiness, whichever occurs 

first. 

(ii) Within 6 months, 1,800 flight hours, or 

1,350 flight cycles after October 11, 2007 (the 

effective date of AD 2007–18–09, 

Amendment 39–15189 (72 FR 51164, 

September 6, 2007)), whichever occurs first. 

(k) Retained Repetitive Inspection Intervals 

for BSCU Standard L4.1 or L4.5 

This paragraph restates the requirements of 

paragraph (j) of AD 2007–18–09, Amendment 

39–15189 (72 FR 51164, September 6, 2007). 

For airplanes not specified in paragraph (h) 

of this AD that are equipped with EMM 

BSCU standard L4.1 or L4.5: Repeat the 

inspection specified in paragraph (j) of this 

AD thereafter at intervals not to exceed the 

earliest of 6 months, 1,800 flight hours, 1,350 

flight cycles, or 100 flight cycles following 

certain ECAM cautions and CFDS messages, 

as specified in paragraph (j)(1) of this AD. 

(l) Retained Repetitive Inspection Intervals 

for BSCU Standard L4.8 or Non-EMM BSCU 

This paragraph restates the requirements of 

paragraph (k) of AD 2007–18–09, 

Amendment 39–15189 (72 FR 51164, 

September 6, 2007). For airplanes not 

specified in paragraph (h) of this AD that are 

equipped with EMM BSCU standard L4.8 or 

a non-EMM BSCU: Repeat the inspection 

specified in paragraph (j) of this AD 

thereafter at intervals not to exceed the 

earliest of 20 months, 6,000 flight hours, 

4,500 flight cycles, or 100 flight cycles 

following certain ECAM cautions and CFDS 

messages, as specified in paragraph (j)(1) of 

this AD. 

(m) Retained Optional Terminating Action 

With Limiting Date Restriction 

This paragraph restates the requirements of 

paragraph (l) of AD 2007–18–09, Amendment 

39–15189 (72 FR 51164, September 6, 2007), 

with a limiting date restriction and specific 

delegation approval language. For airplanes 

that are not specified in paragraph (h) of this 

AD: Installation of an NLG with new upper 

support anti-rotation lugs and new cylinder 

lugs, or installation of an NLG that was never 

driven by EMM BSCU standard L4.1 or L4.5, 

combined with installation of EMM BSCU 

standard L4.8 or a non-EMM BSCU, before 

the effective date of this AD, constitutes 

terminating action for the requirements of 

paragraphs (g), (h), (i), (j), (k), and (l) of this 

AD. Do the installations in accordance with 

a method approved by the Manager, 

International Branch, ANM–116; or EASA; or 

Airbus’s EASA DOA. 

Note 1 to paragraph (m) of this AD: 

Guidance for doing the installation required 

by paragraph (m) of this AD may be found 

in Chapter 32 of the Airbus A318/A319/

A320/A321 Airplane Maintenance Manual. 

(n) Retained Statement of No Reporting 

Requirement 

This paragraph restates the requirements of 

paragraph (m) of AD 2007–18–09, 

Amendment 39–15189 (72 FR 51164, 

September 6, 2007). Although Airbus Service 

Bulletin A320–32–1310, dated February 8, 

2006, specifies sending certain inspection 

results to Airbus, this AD does not include 

that requirement. 

(o) New Part Number Identification 

For the purpose of this AD, the following 

part numbers are identified. 

(1) P/N E21327001 installed by Airbus 

Modification 26965 or by Airbus Service 

Bulletin A320–32–1912 in service stands for 

EMM BSCU L4.1. 

(2) P/N E21327003 installed by Airbus 

Modification 33376 or Airbus Service 

Bulletin A320–32–1261 in service stands for 

EMM BSCU L4.5. 

(3) P/N E21327004 installed by Airbus 

Modification 35216 or Airbus Service 

Bulletin A320–32–1305 or Airbus Service 

Bulletin A320–32–1343/AOT A320–32A1343 

in service stands for EMM BSCU L4.8. 

(4) P/N E213270B1 installed by Airbus 

Modification 31931 or Airbus Service 

Bulletin A320–32–1206 stands for EMM 

BSCU L5–2. 

(5) P/N E21327006 installed by Airbus 

Modification 38973 or Airbus Service 

Bulletin A320–32–1350 or Airbus Service 

Bulletin A320–32–1361 stands for EMM 

BSCU L4.9B. 

(6) P/N E21327106 installed by Airbus 

Modification 151575 or Airbus Service 

Bulletin A320–32–1387 stands for EMM 

BSCU L4.9B. 

(7) P/N C202163392E34 installed by Airbus 

Service Bulletin A320–32–1336 or Airbus 

Service Bulletin A320–32–1360 stands for 

conventional BSCU standard 10. 

(8) P/N C202163392E35 installed by Airbus 

Service Bulletin A320–32–1369 stands for 

conventional BSCU standard 10.1. 

(p) New Records Review 

Within 5 days after the effective date of 

this AD: Perform a records review to 

determine whether the airplane is equipped 

with or has ever been equipped with an EMM 

BSCU having P/N E21327001 (standard L4.1, 

installed by Airbus Modification 26965, or 

Airbus Service Bulletin A320–32–1912); or 

P/N E21327003 (standard L4.5, installed by 

Airbus Modification 33376, or Airbus Service 

Bulletin A320–32–1261); or P/N E21327004 

(standard L4.8, installed by Airbus 

Modification 35216, or Airbus Service 

Bulletin A320–32–1305, or Airbus Service 

Bulletin A320–32–1343/AOT A320– 

32A1343); or P/N E213270B1 (standard L5– 

2, installed by Airbus Modification 31931, or 

Airbus Service Bulletin A320–32–1206). 

(q) New Statement of No Further Action 

Required After Records Review 

For airplanes on which a records review 

required by paragraph (p) of this AD 

conclusively determines that the airplane is 

not and never has been equipped with an 

EMM BSCU having P/N E21327001, P/N 

E21327003, P/N E21327004, or P/N 

E213270B1, no further action is required by 

paragraphs (r) and (s) of this AD. 

(r) New AFM Revision 

For airplanes that are not identified in 

paragraph (q) of this AD and on which 

Airbus Modification 31152 has not been 

incorporated in production (i.e., applicable 

only to aircraft with steering powered by the 

green hydraulic system): Within 10 days after 

the effective date of this AD, revise the 

Limitation Section of the Airbus A318/319/ 

320/321 AFM to include the following 

information. This revision may be done by 

inserting a copy of figure 2 to paragraph (r) 

of this AD into the AFM. Accomplishment of 

the actions required by this paragraph 

terminates the requirements of paragraph (i) 

of this AD, and the AFM revision required by 

paragraph (i) of this AD must be removed. 

When a statement identical to that in figure 

2 to paragraph (r) of this AD has been 

included in the general revisions of the AFM, 

the general revisions may be inserted into the 

AFM, and the copy of figure 2 to paragraph 

(r) of this AD may be removed from the AFM. 

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54586 Federal Register / Vol. 79, No. 177 / Friday, September 12, 2014 / Rules and Regulations 

BILLING CODE 4910–13–C 

(s) New Inspection Following Certain 

Centralized Fault Display System Messages 

(1) For airplanes other than those 

identified in paragraph (q) of this AD: Within 

100 flight cycles following an ECAM caution 

L/G SHOCK ABSORBER FAULT associated 

with at least one of the following CFDS 

messages specified in paragraph (s)(1)(i), 

(s)(1)(ii), or (s)(1)(iii) of this AD, do the 

actions specified in paragraph (s)(2) of this 

AD. 

(i) N L/G EXT PROX SNSR 24GA TGT 

POS. 

(ii) N L/G EXT PROX SNSR 25GA TGT 

POS. 

(iii) N L/G SHOCK ABSORBER FAULT 

2526GM. 

(2) For airplanes identified in paragraph 

(s)(1) of this AD: Do the actions specified in 

paragraphs (s)(2)(i) and (s)(2)(ii) of this AD. 

(i) Check the NLG strut inflation pressure, 

weight-off-wheels, and weight-on-wheels, in 

accordance with the Accomplishment 

Instructions of Airbus Service Bulletin A320– 

32–1310, Revision 01, dated June 23, 2011, 

and before further flight, do all applicable 

corrective actions and adjustments, in 

accordance with Airbus A318/A319/A320/

A321 Airplane Maintenance Manual Task 

12–12–32–610–001–A, Check NLG Shock 

Absorber Fluid Level and Charge Pressure 


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Figure 2 to Paragraph (r) of this AD -New AFM Revision 

The ECAM message, in case of a nose wheel steering failure, will be worded 

as follows: 

-"WHEEL N/W STRG FAULT" for airplanes with Flight Warning Computer 

(FWC) software post E3P. 

-"WHEEL N.W. STEER FAULT" for airplanes with FWC software pre E3P. 

• If the L/G SHOCK ABSORBER FAULT ECAM caution is triggered at any 

time in flight, and the WHEEL N/W STRG FAULT ECAM caution is 

triggered after the landing gear extension: 

• When all landing gear doors are indicated closed on ECAM WHEEL page, 

reset the BSCU: 

- A/SKID&N/W STRG--------------------- OFF THEN ON 

• If the WHEEL N/W STRG FAULT ECAM caution is no longer displayed, 

this indicates a successful nose wheel re-centering and steering recovery. 

- Rearm the AUTO BRAKE, if necessary. 

• If the WHEEL N/W STRG FAULT ECAM caution remains displayed, 

this indicates that the nose wheel steering remains lost, and that the nose 

wheels are not centered. 

- During landing, delay nose wheel touchdown for as long as possible. 

Refer to the ECAM STATUS. 

• Ifthe WHEEL N/W STRG FAULT ECAM caution appears, without 

the L/G SHOCK ABSORBER FAULT ECAM caution: 

-No specific crew action is requested by the WHEEL N/W STRG FAULT 

ECAM caution procedure. 

Refer to the ECAM STATUS. 

Note: For airplanes fitted with pre FWC E3P standard, read N.W STEER 

instead ofN/W STRG. 
Federal Register / Vol. 79, No. 177 / Friday, September 12, 2014 / Rules and Regulations 54587 

(‘‘Two-Point Check’’—Aircraft on Jacks to 

start), Revision August 1, 2012. 

(ii) Do a boroscopic inspection for broken 

or cracked NLG upper support lugs and 

missing or cracked cylinder lugs, and do all 

applicable related investigative and 

corrective actions before further flight. Do all 

actions in accordance with the 

Accomplishment Instructions of Airbus 

Service Bulletin A320–32–1310, Revision 01, 

dated June 23, 2011. Where Airbus Service 

Bulletin A320–32–1310, Revision 01, dated 

June 23, 2011, specifies restoring the NLG in 

accordance with Airbus recommendations, 

this AD requires restoring the NLG before 

further flight, in accordance with a method 

approved by the Manager, International 

Branch, ANM–116, Transport Airplane 

Directorate, FAA; or EASA; or Airbus’s EASA 

DOA. 

(t) New Initial Boroscopic Inspection 

At the applicable times specified in 

paragraphs (t)(1) and (t)(2) of this AD: Do a 

boroscopic inspection for broken or cracked 

NLG upper support lugs and missing or 

cracked cylinder lugs, and do all applicable 

related investigative and corrective actions 

before further flight. Do all actions in 

accordance with the Accomplishment 

Instructions of Airbus Service Bulletin A320– 

32–1310, Revision 01, dated June 23, 2011. 

Where Airbus Service Bulletin A320–32– 

1310, Revision 01, dated June 23, 2011, 

specifies restoring the NLG in accordance 

with Airbus recommendations, this AD 

requires restoring the NLG before further 

flight, in accordance with a method approved 

by the Manager, International Branch, ANM– 

116, Transport Airplane Directorate, FAA; or 

EASA; or Airbus’s EASA DOA. 

Accomplishment of the actions required by 

this paragraph terminate the requirements of 

paragraphs (j), (k), and (l) of this AD. 

(1) For airplanes fitted with twin wheel 

main landing gear (MLG) that have been 

equipped with EMM BSCU standard L4.1, 

L4.5, or L4.8: At the later of the times 

specified in paragraphs (t)(1)(i) and (t)(1)(ii) 

of this AD. 

(i) Within 20 months, or 6,000 flight hours, 

or 4,500 flight cycles since first flight of the 

airplane, whichever occurs first. 

(ii) Within 6 months, or 1,800 flight hours, 

or 1,350 flight cycles after the effective date 

of this AD, whichever occurs first. 

(2) For airplanes fitted with bogie MLG: At 

the later of the times specified in paragraphs 

(t)(2)(i) and (t)(2)(ii) of this AD. 

(i) Within 20 months, or 6,000 flight hours, 

or 4,500 flight cycles after the installation of 

EMM BSCU standard L5–2, whichever occurs 

first. 

(ii) Within 6 months, or 1,800 flight hours, 

or 1,350 flight cycles after the effective date 

of this AD, whichever occurs first. 

(u) New Repetitive Boroscopic Inspections 

After accomplishing the inspection 

specified in paragraph (t) of this AD: Repeat 

the inspection required by paragraph (t) of 

this AD thereafter at the applicable interval 

specified in paragraphs (u)(1), (u)(2), and 

(u)(3) of this AD. 

(1) For airplanes fitted with twin wheel 

MLG that have been equipped with EMM 

BSCU standard L4.8: At intervals not to 

exceed 20 months, or 6,000 flight hours, or 

4,500 flight cycles, whichever occurs first. 

(2) For airplanes fitted with twin wheel 

MLG that have been equipped with EMM 

BSCU standard L4.1 or L4.5: At intervals not 

to exceed 6 months, or 1,800 flight hours, or 

1,350 flight cycles, whichever occurs first. 

(3) For airplanes fitted with bogie MLG: At 

intervals not to exceed 20 months, or 6,000 

flight hours, or 4,500 flight cycles, whichever 

occurs first. 

(v) New Modification 

For airplanes fitted with twin wheel MLG: 

Within 6 months after the effective date of 

this AD, modify the airplane by installing 

EMM BSCU standard L4.9B, in accordance 

with the Accomplishment Instructions of 

Airbus Service Bulletin A320–32–1350, 

dated July 31, 2008. 

(w) New Optional Method of Modification 

Doing a modification specified in 

paragraph (w)(1), (w)(2), or (w)(3) of this AD, 

is acceptable for compliance with the 

requirements of paragraph (v) of this AD. 

(1) Modification of the airplane by 

installing EMM BSCU standard L4.9B, in 

accordance with the Accomplishment 

Instructions of Airbus Service Bulletin A320– 

32–1387, dated April 7, 2011. 

(2) Modification of the airplane by 

installing conventional EMM BSCU standard 

10, in accordance with the Accomplishment 

Instructions of Airbus Service Bulletin A320– 

32–1360, dated March 18, 2009; or Airbus 

Service Bulletin A320–32–1336, Revision 01, 

dated January 10, 2008. 

(3) Modification of the airplane by 

installing conventional EMM BSCU standard 

10.1, in accordance with the 

Accomplishment Instructions of Airbus 

Service Bulletin A320–32–1369, Revision 01, 

dated March 31, 2010. 

(x) New Terminating Action 

In-service modification of an airplane fitted 

with twin wheel MLG, as required by 

paragraph (v) or as specified in paragraph (w) 

of this AD, constitutes terminating action for 

the initial and repetitive inspections required 

by paragraph (t) of this AD. In addition, the 

AFM changes required by paragraph (r) of 

this AD may be removed from the AFM, and 

the requirements of paragraph (s) of this AD 

are no longer required. 

(y) New Exception From Certain Actions 

Except for the prohibition specified in 

paragraph (z) of this AD, airplanes that have 

been delivered with Airbus Modification 

38973 and/or Airbus Modification 151575 

that install EMM BSCU standard L4.9B are 

not affected by the requirements of this AD, 

provided that no installation of previous 

EMM BSCU standard L4.1, L4.5, or L4.8 has 

been performed since the first flight of the 

airplane. 

(z) New Parts Installation Prohibition 

For airplanes on which EMM BSCU L4.1, 

or EMM BSCU L4.5, or EMM BSCU L4.8 is 

not installed: As of the effective date of this 

AD, no person may modify any airplane by 

installing EMM BSCU standard L4.1, L4.5, or 

L4.8. 

(aa) Credit for Previous Actions 

(1) This paragraph restates the 

requirements of paragraph (n) of AD 2007– 

18–09, Amendment 39–15189 (72 FR 51164, 

September 6, 2007). This paragraph provides 

credit for the inspections required by 

paragraph (j) of this AD, if those inspections 

were performed before October 11, 2007 (the 

effective date of AD 2007–18–09), using 

Chapter 12, Subject 12–14–32, of the Airbus 

A318/A319/A320/A321 AMM, as revised by 

Airbus A318/A319/A320/A321 AMM 

Temporary Revision 12–001, dated 

November 13, 2005, which is not 

incorporated by reference in this AD. 

(2) This paragraph provides credit for the 

inspections and related investigative/

corrective actions required by paragraphs (j), 

(k), and (l) of this AD, if those inspections 

were performed before the effective date of 

this AD using Airbus Service Bulletin A320– 

32–1310, dated February 8, 2006. 

(3) This paragraph provides credit for the 

records review required by paragraph (p) of 

this AD, if the review was performed before 

the effective date of this AD using Airbus 

Service Bulletin A320–32–1310, Revision 01, 

dated June 23, 2011. 

(4) This paragraph provides credit for the 

modifications specified in paragraph (w)(2) 

of this AD, if those modifications were 

performed before the effective date of this AD 

using Airbus Service Bulletin A320–32–1336, 

dated September 19, 2007, which is not 

incorporated by reference in this AD. 

(5) This paragraph provides credit for the 

modifications required by paragraph (w)(3) of 

this AD, if those modifications were 

performed before the effective date of this AD 

using Airbus Service Bulletin A320–32–1369, 

dated March 22, 2009, which is not 

incorporated by reference in this AD. 

(bb) 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. 

(i) 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. 

(ii) AMOCs approved previously for AD 

2007–18–09, Amendment 39–15189 (72 FR 

51164, September 6, 2007), are not approved 

as AMOCs with this AD. 

(2) Contacting the Manufacturer: As of the 

effective date of this AD, for any requirement 

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54588 Federal Register / Vol. 79, No. 177 / Friday, September 12, 2014 / Rules and Regulations 

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 EASA; or Airbus’s EASA DOA. If 

approved by the DOA, the approval must 

include the DOA-authorized signature. 

(cc) Related Information 

(1) Refer to Mandatory Continuing 

Airworthiness Information (MCAI) EASA 

Airworthiness Directive 2011–0201, dated 

October 13, 2011, for related information. 

You may examine the MCAI in the AD 

docket on the Internet at http://

www.regulations.gov/

#!documentDetail;D=FAA–2013–0088–0002. 

(2) Service information identified in this 

AD that is not incorporated by reference is 

available at the addresses specified in 

paragraphs (dd)(6) and (dd)(7) of this AD. 

(dd) 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. 

(3) The following service information was 

approved for IBR October 17, 2014. 

(i) Airbus A318/A319/A320/A321 Airplane 

Maintenance Manual Task 12–12–32–610– 

001–A, Check NLG Shock Absorber Fluid 

Level and Charge Pressure (‘‘Two-Point 

Check’’—Aircraft on Jacks to start), Revision 

August 1, 2012. 

(ii) Airbus Service Bulletin A320–32–1310, 

Revision 01, dated June 23, 2011. 

(iii) Airbus Service Bulletin A320–32– 

1336, Revision 01, dated January 10, 2008. 

(iv) Airbus Service Bulletin A320–32– 

1350, dated July 31, 2008. 

(v) Airbus Service Bulletin A320–32–1360, 

dated March 18, 2009. 

(vi) Airbus Service Bulletin A320–32– 

1369, Revision 01, dated March 31, 2010. 

(vii) Airbus Service Bulletin A320–32– 

1387, dated April 7, 2011. 

(4) The following service information was 

approved for IBR on October 11, 2007 (72 FR 

51164, September 6, 2007). 

(i) Airbus Service Bulletin A320–32–1310, 

dated February 8, 2006. 

(ii) Reserved. 

(5) The following service information was 

approved for IBR on November 30, 2005 (70 

FR 70715, November 23, 2005). 

(i) Airbus Technical Note 957.1901/05, 

dated October 18, 2005. 

(ii) Reserved. 

(6) 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. 

(7) 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. 

(8) 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 

November 29, 2013. 

Jeffrey E. Duven, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2014–21552 Filed 9–11–14; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF COMMERCE 

Bureau of the Census 

15 CFR Part 30 

[Docket Number: 140821699–4699–01] 

RIN 0607–AA53 

Foreign Trade Regulations (FTR): 

Reinstatement of Exemptions Related 

to Temporary Exports, Carnets, and 

Shipments Under a Temporary Import 

Bond 

AGENCY: Bureau of the Census, 

Commerce Department. 

ACTION: Interim final rule. 

SUMMARY: The Bureau of the Census 

(Census Bureau) issues this interim final 

rule to amend its regulations to 

eliminate the reporting requirement for 

temporary exports, which includes 

carnets, and goods previously imported 

on a Temporary Importation Under 

Bond (TIB). In the Final Rule published 

in the Federal Register on March 14, 

2013, the Census Bureau removed the 

exemptions for temporary exports, 

which includes carnets and goods 

imported under a TIB. This amendment 

reinstates exemptions for temporary 

exports/carnets and for goods that were 

imported under a TIB for return in the 

same condition as when imported. As a 

result, these types of shipments are 

exempt from filing, except as noted in 

the Foreign Trade Regulations (FTR). 

DATES: Effective date: This interim final 

rule is effective September 12, 2014. 

Comment date: To be assured 

consideration, written comments must 

be received on our before October 14, 

2014. 

ADDRESSES: Please direct all written 

comments on this interim final rule to 

the Chief, Foreign Trade Division, U.S. 

Census Bureau, Room 6K032, 

Washington, DC 20233–6010. You may 

also submit comments, identified by 

RIN 0607–AA53 or by the eRulemaking 

docket number USBC–2014–0003, to the 

Federal e-Rulemaking Portal: http://

www.regulations.gov. All comments 

received are part of the public record. 

No comments will be posted to http:// 

www.regulations.gov for public viewing 

until after the comment period has 

closed. Comments will generally be 

posted without change. All Personally 

Identifiable Information (for example, 

name and address) voluntarily 

submitted by the commenter may be 

publicly accessible. Do not submit 

confidential business information or 

otherwise sensitive or protected 

information. The Census Bureau will 

accept anonymous comments (enter 

N/A in the required fields, if you wish 

to remain anonymous). You may submit 

attachments to electronic comments in 

Microsoft Word, Excel, WordPerfect, or 

Adobe PDF file formats only. 

FOR FURTHER INFORMATION CONTACT: Dale 

C. Kelly, Chief, Foreign Trade Division, 

U.S. Census Bureau, Room 6K032, 

Washington, DC 20233–6010, by phone 

(301) 763–6937, by fax (301) 763–8835, 

or by email <dale.c.kelly@census.gov>. 

SUPPLEMENTARY INFORMATION: 

Background 

The Census Bureau is responsible for 

collecting, compiling, and publishing 

export trade statistics for the United 

States under the provisions of Title 13, 

United States Code (U.S.C.), Chapter 9, 

Section 301. The Automated Export 

System (AES) is the primary instrument 

used for collecting export trade data, 

which are used by the Census Bureau 

for statistical purposes. Through the 

AES, the Census Bureau collects 

Electronic Export Information (EEI), the 

electronic equivalent of the export data 

formerly collected on the Shipper’s 

Export Declaration, pursuant to the 

Foreign Trade Regulations (FTR), Title 

15, Code of Federal Regulations (CFR), 

part 30. Filing in the AES is not 

required for shipments excluded in 

Section 30.2(d) and shipments 

exempted in Subpart D that are not 

subject to Section 30.2(a)(1)(iv). 

The Census Bureau published a Final 

Rule in the Federal Register on March 

14, 2013 (78 FR 16366) that removed the 

exemptions for carnets and other 

temporary exports and goods previously 

imported under a Temporary Import 

Bond (TIB) exported in the same 

condition; it became effective April 5, 

2014. In other words, this rule created 

an AES filing requirement for 

previously exempted items, such as 

carnets. With respect to eliminating 

these exemptions, the Department of the 

Treasury raised concerns and members 

of the trade community submitted 

mstockstill on DSK4VPTVN1PROD with RULES