Federal Register / Vol. 79, No. 48 / Wednesday, March 12, 2014 / Proposed Rules 13925 

1. A Description of the Reasons Action 

by the Agency Is Being Considered 

This proposed AD was prompted by 

failure reports of multiple cylinder 

head-to-barrel separations and cracked 

and leaking aluminum cylinder heads. 

2. Objectives of, and Legal Basis for, the 

Proposed Rule 

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. 

3. A Description of and an Estimate of 

the Number of Small Entities to Which 

the Proposed Rule Will Apply 

The FAA identified 432 small part 

135 operators on which the rule will 

have a significant economic impact. We 

estimate that these small part 135 

operators have assets valued between 

$22 thousand and $21 million. 

4. Reporting, Record Keeping, and Other 

Compliance Requirements of the 

Proposed Rule 

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. Total 

paperwork costs range between $7 and 

$623 per small entity. 

5. Duplicative, Overlapping, or 

Conflicting Federal Rules 

The FAA is unaware of any Federal 

rules that duplicate, overlap, or conflict 

with this rule. 

6. Significant Alternatives to the 

Proposed Rule 

We have considered the following 

alternatives: 

(1) Do nothing—This option is not 

acceptable due to the number of failures 

of ECi cylinder head assemblies and the 

consequences of the failures. 

(2) Periodic inspections only (no 

forced removals)—Though the National 

Transportation Safety Board 

recommends this option, we do not find 

it acceptable. The rate of crack growth 

to failure is unknown, but has shown 

that it can be more rapid than the 

intervals of part 43 mandated 

inspections. Further, failure events tend 

to group in both low time (<500 hr) 

failure events and high time (≤1000 hr) 

failure events. 

(3) Forced removals only (no periodic 

inspections)—We do not find that this 

option is acceptable. Failure events may 

still occur at times other than the low 

and high times groups described above, 

and periodic inspections may find 

impending failures. 

Comments Invited 

We invite you to send any written 

relevant data, views, or arguments about 

this rulemaking. Send your comments to 

an address listed under the ADDRESSES

section. Include ‘‘Docket No. FAA– 

2012–0002; Directorate Identifier 2011– 

NE–42–AD’’ at the beginning of your 

comments. We specifically invite 

comments on the overall regulatory, 

economic, environmental, and energy 

aspects of this rulemaking action. The 

most helpful comments will reference a 

specific portion of the IRFA or related 

rulemaking document, explain the 

reason for any recommended change, 

and include supporting data. 

We will post all comments we 

receive, without change, to http:// 

www.regulations.gov, including any 

personal information you provide. We 

will address all comments in the final 

rule including those already in the AD 

docket from the NPRM. We will also 

post a report summarizing each 

substantive verbal contact we receive 

about the proposed AD. 

Issued in Burlington, Massachusetts, on 

February 27, 2014. 

Colleen M. D’Alessandro, 

Assistant Directorate Manager, Engine & 

Propeller Directorate, Aircraft Certification 

Service. 

[FR Doc. 2014–05234 Filed 3–11–14; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2014–0139; Directorate 

Identifier 2012–NM–133–AD] 

RIN 2120–AA64 

Airworthiness Directives; Airbus 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to supersede 

airworthiness directive (AD) 2009–20– 

05 that applies to certain Model A318, 

A319, A320, and A321 series airplanes. 

AD 2009–20–05 requires one-time 

inspections for cracking, damage, 

correct installation, and correct 

adjustment of the main landing gear 

(MLG) door hinge and actuator fittings 

on the keel beam, and corrective actions 

if necessary. Since we issued AD 2009– 

20–05, we have received reports of 

cracks on fittings that had successfully 

passed the required inspections. This 

proposed AD would expand the 

applicability, reduce the compliance 

time, and require repetitive inspections 

instead of the one-time inspection. This 

proposed AD would also require 

revising the maintenance or inspection 

program to remove a certain 

airworthiness limitations item (ALI) 

task. We are proposing this AD to detect 

and correct such cracking, which could 

lead to in-flight detachment of an MLG 

door, possibly resulting in injury to 

persons on the ground and/or damage to 

the airplane. 

DATES: We must receive comments on 

this proposed AD by April 28, 2014. 

ADDRESSES: You may send comments 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 proposed AD, contact Airbus, 

Airworthiness Office—EIAS, 1 Rond 


tkelley on DSK3SPTVN1PROD with PROPOSALS
13926 Federal Register / Vol. 79, No. 48 / Wednesday, March 12, 2014 / Proposed Rules 

Point Maurice Bellonte, 31707 Blagnac 

Cedex, France; telephone +33 5 61 93 36 

96; fax +33 5 61 93 44 51; email 

account.airworth-eas@airbus.com; 

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

may view this 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– 

0139; or in person at the Docket 

Management Facility between 9 a.m. 

and 5 p.m., Monday through Friday, 

except Federal holidays. The AD docket 

contains this proposed 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: 

Comments Invited 

We invite you to send any written 

relevant data, views, or arguments about 

this proposed AD. Send your comments 

to an address listed under the 

ADDRESSES section. Include ‘‘Docket No. 

FAA–2014–0139; Directorate Identifier 

2012–NM–133–AD’’ at the beginning of 

your comments. We specifically invite 

comments on the overall regulatory, 

economic, environmental, and energy 

aspects of this proposed AD. We will 

consider all comments received by the 

closing date and may amend this 

proposed 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 proposed AD. 

Discussion 

On September 15, 2009, we issued AD 

2009–20–05, Amendment 39–16028 (74 

FR 49795, September 29, 2009). AD 

2009–20–05 requires actions intended to 

address an unsafe condition on certain 

Model A318, A319, A320, and A321 

series airplanes. 

Since we issued AD 2009–20–05, 

Amendment 39–16028 (74 FR 49795, 

September 29, 2009), we have received 

reports of cracks on fittings that had 

successfully passed the required 

inspections. The European Aviation 

Safety Agency (EASA), which is the 

Technical Agent for the Member States 

of the European Community, has issued 

EASA Airworthiness Directive 2012– 

0118, dated July 4, 2012 (referred to 

after this as the Mandatory Continuing 

Airworthiness Information, or ‘‘the 

MCAI’’), to correct an unsafe condition 

for the specified products. The MCAI 

states: 

Several cases of cracks have reportedly 

been found on the MLG door hinge fitting 

and on the MLG door actuator fitting on the 

keel beam. 

This condition, if not detected and 

corrected, could lead to in-flight detachment 

of a MLG door, possibly resulting in injury 

to persons on the ground and/or damage to 

the aeroplane. 

To address this potential unsafe condition, 

EASA issued EASA AD 2007–0161 [http://

ad.easa.europa.eu/blob/easa_ad_2007_0161_

superseded.pdf/AD_2007-0161_1] [which 

corresponds to FAA AD 2009–20–05, 

Amendment 39–16028 (74 FR 49795, 

September 29, 2009)], to require a one-time 

inspection of the affected fittings and 

accomplishment of the applicable corrective 

actions. 

Since that [EASA] AD was issued, some 

cracks have been found on fittings that had 

successfully passed the one-time inspection 

as required by EASA AD 2007–0161. 

Analyses of these cracks have lead Airbus to 

reconsider the repetitive inspections of the 

MLG door hinge and actuator fittings on the 

keel beam, in accordance with the ALI task 

533154–02–1 requirement as defined in 

Airbus A318/A319/A320/A321 

Airworthiness Limitation Items (ALI) 

Document, by introducing more restrictive 

inspection thresholds and intervals. 

For the reasons stated above, this [EASA] 

AD, which supersedes EASA AD 2007–0161 

and the ALI [Airworthiness Limitations Item] 

task 533154–02–1 requirements, expands the 

[EASA] AD applicability to all A318/A319/

A320/A321 aeroplanes and requires 

repetitive inspections of the MLG door hinge 

and actuator fittings on the keel beam at a 

new threshold and interval and, depending 

on findings, the accomplishment of 

applicable corrective actions. 

The inspections are detailed, high 

frequency eddy current (HFEC), and 

ultrasonic inspections for cracking, 

damage, correct installation, and correct 

adjustment, as applicable. The 

corrective actions include correcting 

incorrect adjustments and installations, 

and repair. Additionally, this proposed 

AD would require, for certain airplanes, 

contacting the FAA for instructions on 

repairs and accomplishing those 

instructions. This proposed AD would 

also require revising the maintenance 

program to remove ALI task 533154–02– 

1. You may examine the MCAI in the 

AD docket on the Internet at http://

www.regulations.gov by searching for 

and locating it in Docket No. FAA– 

2014–0139. 

Relevant Service Information 

Airbus has issued Airbus Mandatory 

Service Bulletin A320–53–1195, 

Revision 03, including Service Bulletin 

Reporting Sheet, dated November 8, 

2011; and Airbus Mandatory Service 

Bulletin A320–53–1196, Revision 02, 

including Service Bulletin Reporting 

Sheet, dated November 8, 2011. The 

actions described in this service 

information are intended to correct the 

unsafe condition identified in the 

MCAI. 

FAA’s Determination and Requirements 

of This Proposed 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 proposing this 

AD because we evaluated all pertinent 

information and determined an unsafe 

condition exists and is likely to exist or 

develop on other products of the same 

type design. 

Repair Approvals 

In many FAA transport ADs, when 

the service information specifies to 

contact the manufacturer for further 

instructions if certain discrepancies are 

found, we typically include in the AD 

a requirement to accomplish the action 

using a method approved by either the 

FAA or the State of Design Authority (or 

its delegated agent). 

We have recently been notified that 

certain laws in other countries do not 

allow such delegation of authority, but 

some countries do recognize design 

approval organizations. In addition, we 

have become aware that some U.S. 

operators have used repair instructions 

that were previously approved by a 

State of Design Authority or a Design 

Approval Holder (DAH) as a method of 

compliance with this provision in FAA 

ADs. Frequently, in these cases, the 

previously approved repair instructions 

come from the airplane structural repair 

manual or the DAH repair approval 

statements that were not specifically 

developed to address the unsafe 

condition corrected by the AD. Using 

repair instructions that were not 

specifically approved for a particular 

AD creates the potential for doing 


tkelley on DSK3SPTVN1PROD with PROPOSALS
Federal Register / Vol. 79, No. 48 / Wednesday, March 12, 2014 / Proposed Rules 13927 

repairs that were not developed to 

address the unsafe condition identified 

by the MCAI AD, the FAA AD, or the 

applicable service information, which 

could result in the unsafe condition not 

being fully corrected. 

To prevent the use of repairs that 

were not specifically developed to 

correct the unsafe condition, certain 

requirements specified in this proposed 

AD require that the repair approval 

specifically refer to the FAA AD. This 

change is 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 use the phrase ‘‘its 

delegated agent, or the DAH with State 

of Design Authority design organization 

approval, as applicable’’ in this 

proposed AD to refer to a DAH 

authorized to approve certain required 

repairs for this proposed AD. 

Differences Between This AD and the 

MCAI or Service Information 

The MCAI specifies for airplanes on 

which a Repair Approval Sheet (RAS) 

has been issued by Airbus to cover 

findings from an inspection performed 

before the effective date of this AD, as 

described in certain Airbus documents, 

accomplishing the RAS instructions and 

thereafter doing the repetitive 

inspections specified in the MCAI. This 

proposed AD does not require those 

actions as mandated by the MCAI. 

However, we would like to clarify that 

an RAS issued by the DAH under the 

authority of EASA’s DOA is an 

approved method of repair. This 

difference has been coordinated with 

the EASA. 

Costs of Compliance 

We estimate that this proposed AD 

affects 851 airplanes of U.S. registry. 

The actions that are required by AD 

2009–20–05, Amendment 39–16028 (74 

FR 49795, September 29, 2009), and 

retained in this proposed AD take about 

28 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 2009–20–05 is $2,380 per product. 

We also estimate that it would take 

about 26 work-hours per product to 

comply with the basic requirements of 

this proposed AD. The average labor 

rate is $85 per work-hour. Based on 

these figures, we estimate the cost of 

this proposed AD on U.S. operators to 

be $1,880,710, or $2,210 per product. 

We have received no definitive data 

that would enable us to provide cost 

estimates for the on-condition actions 

specified in this proposed AD. 

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 

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 proposed AD 

would not have federalism implications 

under Executive Order 13132. This 

proposed AD would 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 this proposed regulation: 

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. 

The Proposed Amendment 

Accordingly, under the authority 

delegated to me by the Administrator, 

the FAA proposes to amend 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) 

2009–20–05, Amendment 39–16028 (74 

FR 49795, September 29, 2009), and 

adding the following new AD: 

Airbus: Docket No. FAA–2014–0139; 

Directorate Identifier 2012–NM–133–AD. 

(a) Comments Due Date 

We must receive comments by April 28, 

2014. 

(b) Affected ADs 

This AD supersedes AD 2009–20–05, 

Amendment 39–16028 (74 FR 49795, 

September 29, 2009). 

(c) Applicability 

This AD applies to the Airbus airplanes 

specified in paragraphs (c)(1), (c)(2), (c)(3), 

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

category, all manufacturer 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 A320–211, –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 53, Fuselage. 

(e) Reason 

This AD was prompted by reports of cracks 

on the main landing gear (MLG) door hinge 

fitting and actuator fitting on the keel beam. 

We are issuing this AD to detect and correct 

such cracking, which could lead to in-flight 

detachment of an MLG door, possibly 

resulting in injury to persons on the ground 

and/or damage to the airplane. 


tkelley on DSK3SPTVN1PROD with PROPOSALS
13928 Federal Register / Vol. 79, No. 48 / Wednesday, March 12, 2014 / Proposed Rules 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Retained One-Time Inspections and 

Corrective Action 

This paragraph restates the requirements of 

paragraphs (f)(1) and (f)(2) of AD 2009–20– 

05, Amendment 39–16028 (74 FR 49795, 

September 29, 2009). For airplanes having 

serial numbers up to manufacturer’s serial 

number (MSN) 2850 inclusive, except MSNs 

0115, 0184, 0782, 1151, 1190, 2650, 2675, 

2706, 2801, and 2837: Do the actions 

required by paragraphs (g)(1) and (g)(2) of 

this AD. 

(1) At the latest of the times specified in 

paragraphs (g)(1)(i), (g)(1)(ii), and (g)(1)(iii) of 

this AD: Perform detailed visual, high 

frequency eddy current (HFEC), and 

ultrasonic inspections (for cracking, damage, 

correct installation, and correct adjustment, 

as applicable) of the left-hand (LH) and righthand (RH) MLG door actuator fitting on the 

keel beam, and do all applicable corrective 

actions before further flight, except as 

provided by paragraph (h) of this AD. Do all 

actions required by this paragraph in 

accordance with the Accomplishment 

Instructions of Airbus Mandatory Service 

Bulletin A320–53–1195, Revision 02, 

including Appendix 01, dated April 5, 2007; 

except where that service information 

specifies that the applicable corrective action 

is contacting Airbus, contact Airbus for 

repair instructions and repair before further 

flight. As of the effective date of this AD, 

repair using a method approved by the 

Manager, ANM–116, Transport Airplane 

Directorate, FAA; or the European Aviation 

Safety Agency (EASA) (or its delegated agent, 

or the Design Approval Holder (DAH) with 

the EASA design organization approval, as 

applicable). For a repair method to be 

approved as of the effective date of this AD, 

the repair approval must specifically refer to 

this AD. 

(i) Within 6,000 flight cycles since first 

flight. 

(ii) Within 1,500 flight cycles after 

November 3, 2009 (the effective date of AD 

2009–20–05, Amendment 39–16028 (74 FR 

49795, September 29, 2009)). 

(iii) Within 6,000 flight cycles from the 

latest MLG door actuator fitting replacement. 

(2) At the later of the times specified in 

paragraphs (g)(2)(i) and (g)(2)(ii) of this AD: 

Perform detailed visual and HFEC 

inspections (for cracking, damage, correct 

installation, and correct adjustment, as 

applicable) of the LH and RH MLG door 

hinge fitting on the keel beam, and do all 

applicable corrective actions before further 

flight, except as provided by paragraph (h) of 

this AD. Do all actions required by this 

paragraph in accordance with the 

Accomplishment Instructions of Airbus 

Mandatory Service Bulletin A320–53–1196, 

Revision 01, including Appendix 01, dated 

November 29, 2006; except where that 

service information specifies that the 

applicable corrective action is contacting 

Airbus, contact Airbus for repair instructions 

and repair before further flight. As of the 

effective date of this AD, repair using a 

method approved by the Manager, ANM–116, 

Transport Airplane Directorate, FAA; or the 

European Aviation Safety Agency (EASA) (or 

its delegated agent, or the Design Approval 

Holder (DAH) with the EASA design 

organization approval, as applicable). For a 

repair method to be approved as of the 

effective date of this AD, the repair approval 

must specifically refer to this AD. 

(i) Within 4,500 flight cycles since first 

flight. 

(ii) Within 1,500 flight cycles after 

November 3, 2009 (the effective date of AD 

2009–20–05, Amendment 39–16028 (74 FR 

49795, September 29, 2009)). 

(h) Retained Exception to Paragraph (g) of 

This AD 

This paragraph restates the exception 

specified in paragraph (f)(4) of AD 2009–20– 

05, Amendment 39–16028 (74 FR 49795, 

September 29, 2009). Where the 

Accomplishment Instructions of Airbus 

Mandatory Service Bulletin A320–53–1195, 

Revision 02, including Appendix 01, dated 

April 5, 2007; or Airbus Mandatory Service 

Bulletin A320–53–1196, Revision 01, 

including Appendix 01, dated November 29, 

2006; specify to submit a report where no 

damage or crack is found during the 

inspection required by paragraph (g)(1) or 

(g)(2) of this AD: Send the report to Airbus 

using the applicable reporting sheet in 

Appendix 01 of Airbus Mandatory Service 

Bulletin A320–53–1195, Revision 02, dated 

April 5, 2007; or Airbus Mandatory Service 

Bulletin A320–53–1196, Revision 01, dated 

November 29, 2006. Send the report at the 

applicable time specified in paragraph (h)(1) 

or (h)(2) of this AD. 

(1) If the inspection was done on or after 

November 3, 2009 (the effective date of AD 

2009–20–05, Amendment 39–16028 (74 FR 

49795, September 29, 2009)): Submit the 

report within 30 days after the inspection. 

(2) If the inspection was done before 

November 3, 2009 (the effective date of AD 

2009–20–05, Amendment 39–16028 (74 FR 

49795, September 29, 2009)): Submit the 

report within 30 days after November 3, 

2009. 

(i) New Repetitive Inspections and 

Corrective Action 

(1) At the latest of the times specified in 

paragraphs (i)(1)(i), (i)(1)(ii), and (i)(1)(iii) of 

this AD: Perform detailed, HFEC, and 

ultrasonic inspections (for cracking, damage, 

correct installation, and correct adjustment, 

as applicable) of the LH and RH MLG door 

actuator fitting on the keel beam, and do all 

applicable corrective actions before further 

flight. Do all actions required by this 

paragraph in accordance with the 

Accomplishment Instructions of Airbus 

Mandatory Service Bulletin A320–53–1195, 

Revision 03, including Service Bulletin 

Reporting Sheet, dated November 8, 2011; 

except where that service information 

specifies that the applicable corrective action 

is contacting Airbus, before further flight, 

repair using a method approved by the 

Manager, International Branch, ANM–116, 

Transport Airplane Directorate, FAA; or the 

EASA (or its delegated agent, or the Design 

Approval Holder (DAH) with the EASA 

design organization approval, as applicable). 

For a repair method to be approved, the 

repair approval must specifically refer to this 

AD. Repeat the inspections thereafter at 

intervals not to exceed 2,250 flight cycles. 

(i) Before the accumulation of 3,000 flight 

cycles since first flight. 

(ii) Within 2,250 flight cycles after the most 

recent inspection done as specified in Airbus 

Service Bulletin A320–53–1195, or Task 

533154–02–1 of the Airbus A318/A319/

A320/A321 ALS Part 2—Damage Tolerant 

Airworthiness Limitations Items (DT ALI), as 

applicable. 

(iii) Within 1,500 flight cycles after the 

effective date of this AD. 

(2) At the latest of the times specified in 

paragraphs (i)(2)(i), (i)(2)(ii), and (i)(2)(iii) of 

this AD: Perform detailed and HFEC 

inspections (for cracking, damage, correct 

installation, and correct adjustment, as 

applicable) of the LH and RH MLG door 

hinge fitting on the keel beam, and do all 

applicable corrective actions before further 

flight. Do all actions required by this 

paragraph in accordance with the 

Accomplishment Instructions of Airbus 

Mandatory Service Bulletin A320–53–1196, 

Revision 02, including Service Bulletin 

Reporting Sheet, dated November 8, 2011; 

except where that service information 

specifies that the applicable corrective action 

is contacting Airbus, before further flight, 

repair using a method approved by the 

Manager, International Branch, ANM–116, 

Transport Airplane Directorate, FAA; or the 

EASA (or its delegated agent, or the DAH 

with the EASA design organization approval, 

as applicable). For a repair method to be 

approved, the repair approval must 

specifically refer to this AD. Repeat the 

inspections thereafter at intervals not to 

exceed 3,000 flight cycles. 

(i) Before the accumulation of 3,000 flight 

cycles since first flight. 

(ii) Within 3,000 flight cycles after the most 

recent inspection done as specified in Airbus 

Service Bulletin A320–53–1196, or Task 

533154–02–1 of the Airbus A318/A319/

A320/A321 ALS Part 2—Damage Tolerant 

Airworthiness Limitations Items (DT ALI), as 

applicable. 

(iii) Within 1,500 flight cycles after the 

effective date of this AD. 

(j) New Corrective Action Limitation 

The accomplishment of a corrective action 

on an airplane, as required by paragraph (i) 

of this AD, does not constitute terminating 

action for the repetitive inspection 

requirements of this AD for that airplane. 

(k) New Maintenance or Inspection Program 

Revision 

After the effective date of this AD and 

before further flight after doing the 

inspection required by paragraph (i) of this 

AD: Revise the maintenance or inspection 

program, as applicable, to remove Task 

533154–02–1 of the Airbus A318/A319/

A320/A321 ALS Part 2—Damage Tolerant 

Airworthiness Limitations Items (DT ALI), 

Revision 01, dated April 4, 2012. The actions 

required by this AD take precedence over 

Task 533154–02–1 of the Airbus A318/A319/ 

A320/A321 ALS Part 2—Damage Tolerant 


tkelley on DSK3SPTVN1PROD with PROPOSALS
Federal Register / Vol. 79, No. 48 / Wednesday, March 12, 2014 / Proposed Rules 13929 

Airworthiness Limitations Items (DT ALI), 

Revision 01, dated April 4, 2012. 

(l) 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 district office. The AMOC 

approval letter must specifically reference 

this AD. 

(2) Airworthy Product: For any requirement 

in this AD to obtain corrective actions from 

a manufacturer, use these actions if they are 

FAA-approved. Corrective actions are 

considered FAA-approved if they were 

approved by the State of Design Authority (or 

its delegated agent, or the DAH with a State 

of Design Authority’s design organization 

approval, as applicable). You are required to 

ensure the product is airworthy before it is 

returned to service. 

(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. 

(m) Related Information 

(1) Refer to Mandatory Continuing 

Airworthiness Information European 

Aviation Safety Agency Airworthiness 

Directive 2012–0118, dated July 4, 2012, for 

related information. This MCAI may be 

found in the AD docket on the Internet at 

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

and locating Docket No. FAA–2014–0139. 

(2) 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. 

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. 

Issued in Renton, Washington, on February 

28, 2014. 

Jeffrey E. Duven, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2014–05434 Filed 3–11–14; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2014–0140; Directorate 

Identifier 2013–NM–176–AD] 

RIN 2120–AA64 

Airworthiness Directives; Airbus 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to adopt a new 

airworthiness directive (AD) for certain 

Airbus Model A330–200 and –300 series 

airplanes, and Model A340–200 and 

–300 series airplanes. This proposed AD 

was prompted by a report of contact 

between certain electrical harnesses and 

the hatrack rod that could cause chafing 

between the harnesses and surrounding 

structure. This proposed AD would 

require modifying the routing of certain 

electrical harnesses. We are proposing 

this AD to prevent chafing and possible 

short circuit of two oxygen chemical 

generator containers in different wiring 

routes, which could result in 

malfunction of the electrical opening of 

all the containers connected to these 

routes. Such conditions, during a 

sudden depressurization event, could 

result in lack of oxygen and consequent 

injuries to airplane occupants. 

DATES: We must receive comments on 

this proposed AD by April 28, 2014 

ADDRESSES: You may send comments 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 proposed 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. 

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– 

0140; 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 proposed 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: 

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: 

Comments Invited 

We invite you to send any written 

relevant data, views, or arguments about 

this proposed AD. Send your comments 

to an address listed under the 

ADDRESSES section. Include ‘‘Docket No. 

FAA–2014–0140; Directorate Identifier 

2013–NM–176–AD’’ at the beginning of 

your comments. We specifically invite 

comments on the overall regulatory, 

economic, environmental, and energy 

aspects of this proposed AD. We will 

consider all comments received by the 

closing date and may amend this 

proposed AD based on those comments. 

We will post all comments we 

receive, without change, to http://

www.regulations.gov, including any 


tkelley on DSK3SPTVN1PROD with PROPOSALS