Federal Register / Vol. 79, No. 156 / Wednesday, August 13, 2014 / Proposed Rules 47387 

been in service for less than 60 months, as 

of the effective date of this AD: Before the 

accumulation of 12,000 total flight hours or 

72 months in service, whichever occurs first. 

(h) Terminating Action 

At the applicable time specified in 

paragraph (h)(1) or (h)(2) of this AD: Replace 

all existing aluminum tube assemblies of the 

forward baggage compartment with new, 

improved corrosion-resistant stainless steel 

tube assemblies, in accordance with Part B of 

the Accomplishment Instructions of 

Bombardier Service Bulletin 84–26–15, 

Revision A, dated January 15, 2014, except as 

provided by paragraph (j) of this AD. 

Accomplishing this replacement terminates 

the repetitive inspections required by 

paragraph (g) of this AD. 

(1) For airplanes that have accumulated 

12,000 total flight hours or more, or have 

been in service for 72 months or more, as of 

the effective date of this AD: Within 6,000 

flight hours or 36 months after the effective 

date of this AD, whichever occurs first. 

(2) For airplanes that have accumulated 

less than 12,000 total flight hours, and have 

been in service for less than 72 months, as 

of the effective date of this AD: Before the 

accumulation of 18,000 total flight hours or 

108 months in service, whichever occurs 

first. 

(i) Alternative to Replacement for Failed 

Integrity Check 

As an alternative to the immediate tube 

assembly replacement following any failed 

inspection (integrity check) required by 

paragraph (g) of this AD, the airplane may be 

returned to service for a maximum of 10 

days, provided the conditions specified in 

paragraphs (i)(1), (i)(2), and (i)(3) of this AD 

are met. 

(1) The forward baggage compartment is 

empty. For ballast purposes, the use of bags 

(made of glass fiber or Kevlar) of sand or 

ingots of non-magnetic metals (such as lead) 

are acceptable. 

(2) The flight compartment and forward 

baggage compartment are placarded to 

indicate the forward baggage compartment is 

inoperative. 

(3) An appropriate entry in the aircraft 

maintenance log is made. 

(j) Exception to Service Information 

The electrical bonding resistance check of 

the high rate discharge bottle, as identified in 

Part B of the Accomplishment Instructions of 

Bombardier Service Bulletin 84–26–15, 

Revision A, dated January 15, 2014, is not 

required by this AD. 

(k) Credit for Previous Actions 

This paragraph provides credit for actions 

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

as applicable, if those actions were 

performed before the effective date of this AD 

using Bombardier Service Bulletin 84–26–15, 

dated June 7, 2013, which is not incorporated 

by reference in this AD. 

(l) Other FAA AD Provisions 

The following provisions also apply to this 

AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, New York Aircraft 

Certification Office (ACO), ANE–170, 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 New York ACO, send it to 

ATTN: Program Manager, Continuing 

Operational Safety, FAA, New York ACO, 

1600 Stewart Avenue, Suite 410, Westbury, 

NY 11590; telephone 516–228–7300; fax 

516–794–553. 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) Contacting the Manufacturer: For any 

requirement in this AD to obtain corrective 

actions from a manufacturer, the action must 

be accomplished using a method approved 

by the Manager, New York ACO, ANE–170, 

Engine and Propeller Directorate, FAA; or 

Transport Canada Civil Aviation (TCCA); or 

Bombardier, Inc.’s TCCA Design Approval 

Organization (DAO). If approved by the DAO, 

the approval must include the DAOauthorized signature. 

(m) Related Information 

(1) Refer to Mandatory Continuing 

Airworthiness Information (MCAI) Canadian 

Airworthiness Directive CF–2014–06, dated 

January 21, 2014, 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–2014–0524. 

(2) For service information identified in 

this AD, contact Bombardier, Inc., Q-Series 

Technical Help Desk, 123 Garratt Boulevard, 

Toronto, Ontario M3K 1Y5, Canada; 

telephone 416–375–4000; fax 416–375–4539; 

email thd.qseries@aero.bombardier.com; 

Internet http://www.bombardier.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 July 30, 

2014. 

Jeffrey E. Duven, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2014–19153 Filed 8–12–14; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2014–0525; Directorate 

Identifier 2013–NM–235–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 A330–300 and A340–200 

and –300 series airplanes. This 

proposed AD was prompted by a report 

of substantial inner skin disbonding 

damage found on a rudder. This 

proposed AD would require performing 

an inspection for damage of certain 

rudders, and repair if necessary. We are 

proposing this AD to detect and correct 

damage of the rudder, which could 

result in reduced structural integrity of 

the rudder. 

DATES: We must receive comments on 

this proposed AD by September 29, 

2014. 

ADDRESSES: You may send comments, 

using the procedures found in 14 CFR 

11.43 and 11.45, by any of the following 

methods: 

• Federal eRulemaking Portal: Go to 

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

instructions for submitting comments. 

• Fax: 202–493–2251. 

• Mail: U.S. Department of 

Transportation, Docket Operations, M– 

30, West Building Ground Floor, Room 

W12–140, 1200 New Jersey Avenue SE., 

Washington, DC 20590. 

• Hand Delivery: U.S. Department of 

Transportation, Docket Operations, M– 

30, West Building Ground Floor, Room 

W12–140, 1200 New Jersey Avenue SE., 

Washington, DC, between 9 a.m. and 5 

p.m., Monday through Friday, except 

Federal holidays. 

For service information identified in 

this 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. 


wreier-aviles on DSK5TPTVN1PROD with PROPOSALS
47388 Federal Register / Vol. 79, No. 156 / Wednesday, August 13, 2014 / Proposed Rules 

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– 

0525; 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: 

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–2014–0525; Directorate Identifier 

2013–NM–235–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 

The European Aviation Safety Agency 

(EASA), which is the Technical Agent 

for the Member States of the European 

Community, has issued EASA 

Airworthiness Directive 2013–0270R1, 

dated November 27, 2013 (referred to 

after this as the Mandatory Continuing 

Airworthiness Information, or ‘‘the 

MCAI’’), to correct an unsafe condition 

for certain Airbus Model A330–300 and 

A340–200 and –300 series airplanes. 

The MCAI states: 

One A310 operator found substantial inner 

skin disbonding damage on a rudder. The 

results of the subsequent investigation 

revealed that the most probable cause of this 

damage was a blunt impact with no visible 

damage from outside during the rudder 

handling. Such type of damage might grow 

with pressure variation during ground-airground cycles, and tests performed with 

other rudders showed a rapid propagation of 

damage during artificial pressure cycling. 

This condition, if not detected and 

corrected, could affect the structural integrity 

of the rudder. 

For the affected A310 and A300–600 

aeroplanes, EASA issued AD 2013–0039 

[(http://ad.easa.europa.eu/blob/easa_ad_

2013_0039.pdf/AD_2013–0039)], to address 

and correct this potential unsafe condition. 

As potentially affected rudders can also be 

installed on A330 and A340 aeroplanes, 

Airbus issued Alert Operator Transmission 

(AOT) A55L001–12 [dated December 20, 

2012], pending Aircraft Maintenance Manual 

(AMM) 27–21–41 PB401 revision, to provide 

operators with updated rudder handling 

procedures. 

EASA issued AD 2013–0270 [(http://

ad.easa.europa.eu/blob/easa_ad_2013_

0270.pdf/AD_2013–0270)], to require 

identification of affected rudders P/N [part 

number] A55471500XXX (where XXX stands 

for any numerical value), a one-time 

ultrasonic test (UT) inspection of each 

affected rudder to detect signs of disbonding 

and, depending on findings, accomplishment 

of applicable corrective action(s). 

After [EASA] AD 2013–0270 was issued, 

operators commented that the batch of 

rudders to be inspected was not correctly 

defined. 

For the reason described above, [EASA] AD 

2013–0270 is revised to clarify that no action 

is required for rudders previously inspected 

in accordance with Airbus Service Bulletin 

(ASB) A330–55–3038 [dated November 7, 

2007] or SB A340–55–4034 [dated November 

7, 2007] [which corresponds to FAA AD 

2009–10–11, Amendment 39–15907 (74 FR 

23622, May 20, 2009)], as applicable to 

aeroplane model, provided the rudder has 

never been removed and/or installed on an 

aeroplane since this inspection. 

Required actions include an elasticity 

of laminate checker inspection of the 

rudder side panel to detect external and 

internal disbonding, and a woodpecker 

or tap test inspection to detect external 

disbonding, and repair if necessary. You 

may examine the MCAI in the AD 

docket on the Internet at http://

www.regulations.gov by searching for 

and locating Docket No. FAA–2014– 

0525. 

Relevant Service Information 

Airbus has issued Alert Operators 

Transmission A55L001–12, dated 

December 20, 2012. 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. 

‘‘Contacting the Manufacturer’’ 

Paragraph in This Proposed 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. 

The MCAI or referenced service 

information in an FAA AD often directs 

the owner/operator to contact the 

manufacturer for corrective actions, 

such as a repair. Briefly, the Airworthy 

Product paragraph allowed owners/

operators to use corrective actions 

provided by the manufacturer if those 

actions were FAA-approved. In 

addition, the paragraph stated that any 

actions approved by the State of Design 

Authority (or its delegated agent) are 

considered to be FAA-approved. 

In an NPRM having Directorate 

Identifier 2012–NM–101–AD (78 FR 

78285, December 26, 2013), we 

proposed to prevent the use of repairs 

that were not specifically developed to 

correct the unsafe condition, by 

requiring that the repair approval 

provided by the State of Design 

Authority or its delegated agent 

specifically refer to the FAA AD. This 

change was intended to clarify the 

method of compliance and to provide 

operators with better visibility of repairs 

that are specifically developed and 

approved to correct the unsafe 

condition. In addition, we proposed to 

change the phrase ‘‘its delegated agent’’ 

to include a design approval holder 

(DAH) with State of Design Authority 

design organization approval (DOA), as 

applicable, to refer to a DAH authorized 

to approve required repairs for the 

proposed AD. 

One commenter to the NPRM having 

Directorate Identifier 2012–NM–101–AD 

(78 FR 78285, December 26, 2013) stated 

the following: ‘‘The proposed wording, 

being specific to repairs, eliminates the 

interpretation that Airbus messages are 

acceptable for approving minor 

deviations (corrective actions) needed 

during accomplishment of an AD 

mandated Airbus service bulletin.’’ 

This comment has made the FAA 

aware that some operators have 

misunderstood or misinterpreted the 

Airworthy Product paragraph to allow 

the owner/operator to use messages 


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Federal Register / Vol. 79, No. 156 / Wednesday, August 13, 2014 / Proposed Rules 47389 

provided by the manufacturer as 

approval of deviations during the 

accomplishment of an AD-mandated 

action. The Airworthy Product 

paragraph does not approve messages or 

other information provided by the 

manufacturer for deviations to the 

requirements of the AD-mandated 

actions. The Airworthy Product 

paragraph only addresses the 

requirement to contact the manufacturer 

for corrective actions for the identified 

unsafe condition and does not cover 

deviations from other AD requirements. 

However, deviations to AD-required 

actions are addressed in 14 CFR 39.17, 

and anyone may request the approval 

for an alternative method of compliance 

to the AD-required actions using the 

procedures found in 14 CFR 39.19. 

To address this misunderstanding and 

misinterpretation of the Airworthy 

Product paragraph, we have changed the 

paragraph and retitled it ‘‘Contacting the 

Manufacturer.’’ This paragraph now 

clarifies that for any requirement in this 

proposed AD to obtain corrective 

actions from a manufacturer, the action 

must be accomplished using a method 

approved by the FAA, the European 

Aviation Safety Agency (EASA), or 

Airbus’s EASA DOA. 

The Contacting the Manufacturer 

paragraph also clarifies that, if approved 

by the DOA, the approval must include 

the DOA-authorized signature. The DOA 

signature indicates that the data and 

information contained in the document 

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

information provided by the 

manufacturer that do not contain the 

DOA-authorized signature approval are 

not EASA-approved, unless EASA 

directly approves the manufacturer’s 

message or other information. 

This clarification does not remove 

flexibility previously afforded by the 

Airworthy Product paragraph. 

Consistent with long-standing FAA 

policy, such flexibility was never 

intended for required actions. This is 

also consistent with the 

recommendation of the Airworthiness 

Directive Implementation Aviation 

Rulemaking Committee to increase 

flexibility in complying with ADs by 

identifying those actions in 

manufacturers’ service instructions that 

are ‘‘Required for Compliance’’ with 

ADs. We continue to work with 

manufacturers to implement this 

recommendation. But once we 

determine that an action is required, any 

deviation from the requirement must be 

approved as an alternative method of 

compliance. 

Costs of Compliance 

We estimate that this proposed AD 

affects 74 airplanes of U.S. registry. 

We also estimate that it would take 

about 12 work-hours per product to 

comply with the basic requirements of 

this proposed AD. The average labor 

rate is $85 per work-hour. Required 

parts would cost about $0 per product. 

Based on these figures, we estimate the 

cost of this proposed AD on U.S. 

operators to be $75,480, or $1,020 per 

product. 

We have received no definitive data 

that would enable us to provide a cost 

estimate for the on-condition actions 

specified in this proposed AD. 

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 adding 

the following new airworthiness 

directive (AD): 

Airbus: Docket No. FAA–2014–0525; 

Directorate Identifier 2013–NM–235–AD. 

(a) Comments Due Date 

We must receive comments by September 

29, 2014. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to Airbus Model A330– 

301, –302, –303, –321, –322, –323, –341, 

–342, and –343 airplanes; and Model A340– 

211, –212, –213, –311, –312, and –313 

airplanes; certificated in any category; except 

airplanes on which Airbus Modification 

41800 has been embodied in production. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 55, Stabilizers. 

(e) Reason 

This AD was prompted by a report of 

substantial inner skin disbonding damage on 

a rudder. We are issuing this AD to detect 

and correct damage of the rudder, which 

could result in reduced structural integrity of 

the rudder. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Rudder Assembly Identification 

Within 3 months after the effective date of 

this AD, inspect for the rudder assembly part 

number and serial number, in accordance 

with Airbus Alert Operators Transmission 

(AOT) A55L001–12, dated December 20, 

2012. If the part number or serial number 

cannot be identified, before further flight, 

identify the part number and serial number 

using a method approved by the Manager, 

International Branch, ANM–116, Transport 

Airplane Directorate, FAA; or the European 

Aviation Safety Agency (EASA); or Airbus’s 

EASA Design Organization Approval (DOA). 

If approved by the DOA, the approval must 

include the DOA-authorized signature. 


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47390 Federal Register / Vol. 79, No. 156 / Wednesday, August 13, 2014 / Proposed Rules 

(h) Inspection 

If a rudder assembly having any part 

number starting with A55471500 or 

A55471500XXX (where XXX stands for any 

numerical value) is found during the 

inspection required by paragraph (g) of this 

AD, and has been inspected before the 

effective date of this AD, as specified in 

Airbus Service Bulletin A300–55–3038, 

dated November 7, 2007; or Airbus Service 

Bulletin A310–55–4034, dated November 7, 

2007; as applicable; and has been removed 

and installed on any airplane after the 

inspection, or that rudder has been inspected 

off-wing: Before further flight, do an 

ultrasonic test inspection for damage (e.g., 

disbonding and liquid ingress) of the rudder 

side panel along the Z-profile and in the 

booster area, in accordance with Airbus AOT 

A55L001–12, dated December 20, 2012. If 

any damage is found, before further flight, do 

the inspections specified in paragraphs (h)(1) 

and (h)(2) of this AD to confirm disbonding 

damage, in accordance with AOT A55L001– 

12, dated December 20, 2012. 

(1) Do an elasticity of laminate checker 

inspection to detect external and internal 

disbonding. 

(2) Do a woodpecker or tap test inspection 

to detect external disbonding. 

(i) Repair 

If any disbonding or damage (e.g. liquid 

ingress) is confirmed during any inspection 

required by paragraphs (h), (h)(1), and (h)(2) 

of this AD, repair at the time specified in 

paragraph (i)(1), (i)(2), or (i)(3) of this AD, as 

applicable. 

(1) If the disbonding is less than or equal 

to 50 millimeters (mm) in width and less 

than or equal to 150 mm in length: Before 

further flight, vent the rudder core using a 

method approved by the Manager, 

International Branch, ANM–116, Transport 

Airplane Directorate, FAA; or EASA; or 

Airbus’s EASA DOA. Within 100 flight cycles 

after venting the rudder core, do a permanent 

repair using a method approved by the 

Manager, International Branch, ANM–116, 

Transport Airplane Directorate, FAA; or 

EASA; or Airbus’s EASA DOA. If approved 

by the DOA, the approval for the venting and 

repair methods must include the DOAauthorized signature. 

(2) If the disbonding is greater than 50mm 

in width, or greater than 150 mm in length: 

Before further flight, repair using a method 

approved by the Manager, International 

Branch, ANM–116, Transport Airplane 

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

DOA. If approved by the DOA, the approval 

must include the DOA-authorized signature. 

(3) If any damage other than disbonding 

(e.g., liquid ingress) is confirmed during any 

inspection required by paragraph (h) of this 

AD, before further flight, repair, using a 

method approved by the Manager, 

International Branch, ANM–116, Transport 

Airplane Directorate, FAA; or EASA; or 

Airbus’s EASA DOA. If approved by the 

DOA, the approval must include the DOAauthorized signature. 

(j) Parts Installation Limitation 

As of the effective date of this AD, you may 

install, on any airplane, a rudder assembly 

having part number A55471500XXX (where 

XXX stands for any numerical value), 

provided the inspection required by 

paragraph (h) of this AD and all applicable 

repair actions required by paragraph (i) of 

this AD are done before further flight. 

(k) Other FAA AD Provisions 

The following provisions also apply to this 

AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, International 

Branch, ANM–116, Tranport Airplane 

Directorate, FAA, has the authority to 

approve AMOCs for this AD, if requested 

using the procedures found in 14 CFR 39.19. 

In accordance with 14 CFR 39.19, send your 

request to your principal inspector or local 

Flight Standards District Office, as 

appropriate. If sending information directly 

to the International Branch, send it to ATTN: 

Vladimir Ulyanov, Aerospace Engineer, 

International Branch, ANM–116, Transport 

Airplane Directorate, FAA, 1601 Lind 

Avenue SW., Renton, WA 98057–3356; 

telephone (425) 227–1138; fax (425) 227– 

1149. Information may be emailed to: 9- 

ANM-116-AMOC-REQUESTS@faa.gov. 

Before using any approved AMOC, notify 

your appropriate principal inspector, or 

lacking a principal inspector, the manager of 

the local flight standards district office/

certificate holding district office. The AMOC 

approval letter must specifically reference 

this AD. 

(2) Contacting the Manufacturer: For any 

requirement in this AD to obtain corrective 

actions from a manufacturer, the action must 

be accomplished using a method approved 

by the Manager, International Branch, ANM– 

116, Transport Airplane Directorate, FAA; or 

EASA; or Airbus’s EASA DOA. If approved 

by the DOA, the approval must include the 

DOA-authorized signature. 

(l) Related Information 

(1) Refer to Mandatory Continuing 

Airworthiness Information (MCAI) EASA 

Airworthiness Directive 2013–0270R1, dated 

November 27, 2013, 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–2014–0525. 

(2) For service information identified in 

this AD, contact Airbus SAS, Airworthiness 

Office—EAL, 1 Rond Point Maurice Bellonte, 

31707 Blagnac Cedex, France; telephone +33 

5 61 93 36 96; fax +33 5 61 93 45 80; email 

airworthiness.A330-A340@airbus.com; 

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

view this 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 July 30, 

2014. 

Jeffrey E. Duven, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2014–19155 Filed 8–12–14; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2014–0530; Directorate 

Identifier 2014–NM–062–AD] 

RIN 2120–AA64 

Airworthiness Directives; ATR—GIE 

Avions de Transport Re ́gional 

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 

ATR—GIE Avions de Transport 

Re ́gional Model ATR42–500 airplanes, 

and Model ATR72–212A airplanes. This 

proposed AD was prompted by a report 

that during an inspection of an airplane 

on the production line, interference was 

detected between the electrical harness 

and a bonding lead due to an incorrect 

installation of the affected bonding lead. 

This proposed AD would require a 

detailed inspection for damage or 

incorrect routing of the bonding lead 

routing above the 120VU shelf, and if 

any damage or incorrect routing is 

found, modifying the bonding lead 

routing. We are proposing this AD to 

detect and correct installation of the 

bonding lead, which could cause arcing 

and chafing, and could possibly result 

in an uncontrolled fire. 

DATES: We must receive comments on 

this proposed AD by September 29, 

2014. 

ADDRESSES: You may send comments, 

using the procedures found in 14 CFR 

11.43 and 11.45, by any of the following 

methods: 

• Federal eRulemaking Portal: Go to 

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

instructions for submitting comments. 

• Fax: 202–493–2251. 

• Mail: U.S. Department of 

Transportation, Docket Operations, M– 

30, West Building Ground Floor, Room 

W12–140, 1200 New Jersey Avenue SE., 

Washington, DC 20590. 

• Hand Delivery: U.S. Department of 

Transportation, Docket Operations, M– 

30, West Building Ground Floor, Room 

W12–140, 1200 New Jersey Avenue SE., 

Washington, DC, between 9 a.m. and 5 

p.m., Monday through Friday, except 

Federal holidays. 

For service information identified in 

this proposed AD, contact ATR—GIE 

Avions de Transport Re ́gional, 1, Alle ́e 

Pierre Nadot, 31712 Blagnac Cedex, 

France; telephone +33 (0) 5 62 21 62 21; 


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