Federal Register / Vol. 81, No. 40 / Tuesday, March 1, 2016 / Proposed Rules 10537 

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): 

Dassault Aviation: Docket No. FAA–2016– 

3987; Directorate Identifier 2015–NM– 

165–AD. 

(a) Comments Due Date 

We must receive comments by April 15, 

2016. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to Dassault Aviation 

Model FALCON 7X airplanes, certificated in 

any category, manufacturer serial numbers 1 

through 221 inclusive, except serial numbers 

182 and 220. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 53, Fuselage. 

(e) Reason 

This AD was prompted by a report of 

improperly drilled bores, located on upper 

and lower stiffener joints to the web at a 

certain frame. We are issuing this AD to 

detect and correct an unsatisfactory bore that 

can adversely affect the structural integrity of 

the airplane. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Inspect Bores 

Within 4,000 flight cycles or 98 months, 

whichever occurs first since date of issuance 

of the original airworthiness certificate or 

date of issuance of the original export 

certificate of airworthiness, do a detailed 

visual and rototest inspection of the bores, 

located on upper and lower stiffener joints to 

the web at pylon Frame 41, to determine if 

the bores are not satisfactory, in accordance 

with the Accomplishment Instructions of 

Dassault Service Bulletin 7X–346, dated 

April 24, 2015. 

(h) Repair 

If, during the inspection required by 

paragraph (g) of this AD, it is determined that 

any bore is not satisfactory: Before further 

flight, repair affected bores, in accordance 

with the Accomplishment Instructions of 

Dassault Service Bulletin 7X–346, dated 

April 24, 2015, except as required by 

paragraph (i) of this AD. 

(i) Exceptions 

Where the Dassault Service Bulletin 7X– 

346, dated April 24, 2015, specifies to contact 

Dassault Aviation: Before further flight, 

repair using a method approved by the 

Manager, International Branch, ANM–116, 

Transport Airplane Directorate, FAA; or the 

European Aviation Safety Agency (EASA); or 

Dassault Aviation’s EASA Design 

Organization Approval (DOA). 

(j) 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: 

Tom Rodriguez, Aerospace Engineer, 

International Branch, ANM–116, Transport 

Airplane Directorate, FAA, 1601 Lind 

Avenue SW., Renton, WA 98057–3356; 

telephone 425–227–1137; 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 Dassault Aviation’s EASA DOA. If 

approved by the DOA, the approval must 

include the DOA-authorized signature. 

(k) Related Information 

(1) Refer to Mandatory Continuing 

Airworthiness Information (MCAI) EASA AD 

2015–0204, dated October 8, 2015, for related 

information. This MCAI may be found on the 

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

searching for and locating Docket No. FAA– 

2016–3987. 

(2) For service information identified in 

this AD, contact Dassault Falcon Jet 

Corporation, Teterboro Airport, P.O. Box 

2000, South Hackensack, NJ 07606; 

telephone: 201–440–6700; Internet: http://

www.dassaultfalcon.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 

19, 2016. 

Dorr M. Anderson, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2016–04295 Filed 2–29–16; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2016–3986; Directorate 

Identifier 2015–NM–147–AD] 

RIN 2120–AA64 

Airworthiness Directives; The Boeing 

Company 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 

The Boeing Company Model 747–400, 

747–400D, and 747–400F series 

airplanes. This proposed AD was 

prompted by a determination that a 

certain fastener type in the fuel tank 

walls has insufficient bond to the 

structure, and an electrical wiring short 

could cause arcing to occur at the ends 

of fasteners in the fuel tanks. This 

proposed AD would require the 

installation of new clamps and 

polytetrafluoroethylene (TFE) sleeves on 

the wire bundles of the front spars and 

rear spars of the wings. This proposed 

AD would also require inspecting the 

existing TFE sleeves under the wire 

bundle clamps for correct installation, 

and replacement if necessary. We are 

proposing this AD to prevent potential 

ignition sources in the fuel tank in the 

event of a lightning strike or highpowered short circuit, and consequent 

fire or explosion. 


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10538 Federal Register / Vol. 81, No. 40 / Tuesday, March 1, 2016 / Proposed Rules 

DATES: We must receive comments on 

this proposed AD by April 15, 2016. 

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: Deliver to Mail 

address above between 9 a.m. and 5 

p.m., Monday through Friday, except 

Federal holidays. 

For service information identified in 

this NPRM, contact Boeing Commercial 

Airplanes, Attention: Data & Services 

Management, P.O. Box 3707, MC 2H–65, 

Seattle, WA 98124–2207; telephone 

206–544–5000, extension 1; fax 206– 

766–5680; Internet https://

www.myboeingfleet.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. It is also available 

on the Internet at http://

www.regulations.gov by searching for 

and locating Docket No. FAA–2016– 

3986. 

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–2016– 

3986; 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 Office 

(phone: 800–647–5527) is in the 

ADDRESSES section. Comments will be 

available in the AD docket shortly after 

receipt. 

FOR FURTHER INFORMATION CONTACT: 

Tung Tran, Aerospace Engineer, 

Propulsion Branch, ANM–140S, FAA, 

Seattle Aircraft Certification Office 

(ACO), 1601 Lind Avenue SW., Renton, 

WA 98057–3356; phone: 425–917–6505; 

fax: 425–917–6590; email: Tung.Tran@

faa.gov. 

SUPPLEMENTARY INFORMATION: 

Comments Invited 

We invite you to send any written 

relevant data, views, or arguments about 

this proposal. Send your comments to 

an address listed under the ADDRESSES

section. Include ‘‘Docket No. FAA– 

2016–3986; Directorate Identifier 2015– 

NM–147–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 because of 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 manufacturer has determined that 

a certain fastener type in the fuel tank 

walls has insufficient bond to the 

structure, and an electrical wiring short 

could cause arcing to occur at the ends 

of fasteners in the fuel tanks. Potential 

ignition sources in the fuel tank in the 

event of a lightning strike or highpowered short circuit, if not corrected, 

could result in a fire or explosion. 

Related Rulemaking 

On September 17, 2007, we issued AD 

2007–20–01, Amendment 39–15211 (72 

FR 54533, September 26, 2007), 

applicable to certain The Boeing 

Company Model 747–100B SUD, 747– 

200B, 747–200C, 747–200F, 747–300, 

747–400, 747–400D, 747–400F, and 

747SP series airplanes. That AD 

requires reconfiguring the clamps of 

certain wire bundles and applying 

insulating sealant to certain fasteners 

inside the fuel tanks using Boeing 

Special Attention Service Bulletin 747– 

57–2327, Revision 1, dated July 10, 

2006, on airplane line numbers 696 

through 1363. Airplane line numbers 

1364 through 1419 were changed during 

production. The actions required by AD 

2007–20–01 are intended to prevent 

arcing inside the fuel tanks in the event 

of a lightning strike or high-powered 

short circuit, which could result in a 

fuel tank explosion or fire. 

Since we issued AD 2007–20–01, 

Amendment 39–15211 (72 FR 54533, 

September 26, 2007), the FAA has 

determined that for certain The Boeing 

Company Model 747–400, 747–400D, 

and 747–400F series airplanes, a certain 

fastener type in the fuel tank walls has 

insufficient bond to the structure and 

that an electrical wiring short could 

cause arcing to occur at the ends of 

fasteners in the fuel tanks. We 

determined that certain clamp locations 

need to be changed to prevent possible 

ignition sources in the fuel tanks. These 

clamps were not installed at these 

locations during production and were 

not identified in Boeing Special 

Attention Service Bulletin 747–57– 

2327, Revision 1, dated July 10, 2006. 

Therefore, it is necessary to install new 

clamps and TFE sleeves at these 

additional locations on the wire bundles 

of the front spars and rear spars of the 

left and right wings. 

Related Service Information Under 1 

CFR Part 51 

We reviewed Boeing Special 

Attention Service Bulletin 747–28– 

2324, Revision 1, dated July 27, 2015. 

The service information describes 

procedures for installing new clamps 

and TFE sleeves on the wire bundles of 

the front spars and rear spars of the 

wings. The service information also 

describes procedures for inspecting TFE 

sleeves under the wire bundle clamps 

that were installed using the procedures 

specified in Boeing Special Attention 

Service Bulletin 747–28–2324, dated 

November 4, 2014, for correct 

installation, and replacing them if 

necessary. This service information is 

reasonably available because the 

interested parties have access to it 

through their normal course of business 

or by the means identified in the 

ADDRESSES section. 

FAA’s Determination 

We are proposing this AD because we 

evaluated all the relevant information 

and determined the unsafe condition 

described previously is likely to exist or 

develop in other products of the same 

type design. 

Proposed AD Requirements 

This proposed AD would require 

accomplishing the actions specified in 

the service information described 

previously. 

Costs of Compliance 

We estimate that this proposed AD 

affects 135 airplanes of U.S. registry. 

We estimate the following costs to 

comply with this proposed AD: 


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Federal Register / Vol. 81, No. 40 / Tuesday, March 1, 2016 / Proposed Rules 10539 

ESTIMATED COSTS

Action Labor cost Parts cost Cost per 

product 

Cost on U.S. operators 

Installation of wire bundle clamps Up to 7 work-hours × $85 per hour = $595 .............. $138 Up to $733 ....... Up to $98,955. 

Inspection ...................................... Up to 5 work-hours × $85 per hour = $425 .............. $0 Up to $425 ....... Up to $57,375. 

We have received no definitive data 

that would enable us to provide cost 

estimates 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): 

The Boeing Company: Docket No. FAA– 

2016–3986; Directorate Identifier 2015– 

NM–147–AD. 

(a) Comments Due Date 

We must receive comments by April 15, 

2016. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to The Boeing Company 

Model 747–400, 747–400D, and 747–400F 

series airplanes, certificated in any category, 

as identified in Boeing Special Attention 

Service Bulletin 747–28–2324, Revision 1, 

dated July 27, 2015. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 28, Fuel. 

(e) Unsafe Condition 

This AD was prompted by a determination 

that a certain fastener type in the fuel tank 

walls has insufficient bond to the structure, 

and an electrical wiring short could cause 

arcing to occur at the ends of fasteners in the 

fuel tanks. We are issuing this AD to prevent 

potential ignition sources in the fuel tank in 

the event of a lightning strike or highpowered short circuit, and consequent fire or 

explosion. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Installation/Inspection 

Within 60 months after the effective date 

of this AD, do the actions specified in 

paragraph (g)(1) or (g)(2) of this AD, as 

applicable. 

(1) For airplanes on which the 

modification specified in Boeing Special 

Attention Service Bulletin 747–28–2324, 

dated November 3, 2014, has not been done 

as of the effective date of this AD: Install new 

clamps and polytetrafluoroethylene (TFE) 

sleeves on the wire bundles of the front spars 

and rear spars of the wings, in accordance 

with the Accomplishment Instructions of 

Boeing Special Attention Service Bulletin 

747–28–2324, Revision 1, dated July 27, 

2015. 

(2) For airplanes on which the 

modification specified in Boeing Special 

Attention Service Bulletin 747–28–2324, 

dated November 3, 2014, has been done as 

of the effective date of this AD: Do a detailed 

inspection of the TFE sleeves under the wire 

bundle clamps for correct installation, and 

replace the sleeves if not correctly installed, 

in accordance with the Accomplishment 

Instructions of Boeing Special Attention 

Service Bulletin 747–28–2324, Revision 1, 

dated July 27, 2015. 

(h) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Seattle Aircraft 

Certification Office (ACO), 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 manager of the ACO, send it to the 

attention of the person identified in 

paragraph (i)(1) of this AD. Information may 

be emailed to: 9-ANM-Seattle-ACO-AMOCRequests@faa.gov. 

(2) 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. 

(3) An AMOC that provides an acceptable 

level of safety may be used for any repair, 

alteration, or modification required by this 

AD if it is approved by the Boeing 

Commercial Airplanes Organization 

Designation Authorization (ODA) that has 

been authorized by the Manager, Seattle 

ACO, to make those findings. For a repair 

method to be approved, the repair method, 

modification deviation, or alteration 

deviation must meet the certification basis of 

the airplane, and the approval must 

specifically refer to this AD. 

(i) Related Information 

(1) For more information about this AD, 

contact Tung Tran, Aerospace Engineer, 

Propulsion Branch, ANM–140S, FAA, Seattle 

Aircraft Certification Office (ACO), 1601 Lind 

Avenue SW., Renton, WA 98057–3356; 

phone: 425–917–6505; fax: 425–917–6590; 

email: Tung.Tran@faa.gov. 

(2) For service information identified in 

this AD, contact Boeing Commercial 

Airplanes, Attention: Data & Services 


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10540 Federal Register / Vol. 81, No. 40 / Tuesday, March 1, 2016 / Proposed Rules 

Management, P.O. Box 3707, MC 2H–65, 

Seattle, WA 98124–2207; telephone 206– 

544–5000, extension 1; fax 206–766–5680; 

Internet https://www.myboeingfleet.com. You 

may view this referenced service information 

at the FAA, Transport Airplane Directorate, 

1601 Lind Avenue SW., Renton, Washington. 

For information on the availability of this 

material at the FAA, call 425–227–1221. 

Issued in Renton, Washington, on February 

19, 2016. 

Dorr M. Anderson, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2016–04292 Filed 2–29–16; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2016–3984; Directorate 

Identifier 2014–NM–119–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) 2013–10– 

03, for all Airbus Model A330–200, 

–200 Freighter, and –300 series 

airplanes; and Model A340–200, –300, 

–500, and –600 series airplanes. AD 

2013–10–03 currently requires one-time 

inspections for deformation and damage 

of the bogie beams of the main landing 

gear (MLG); repetitive inspections for 

damage and corrosion of the sliding 

piston sub-assembly on certain 

airplanes; and related investigative and 

corrective actions if necessary. Since we 

issued AD 2013–10–03, we have 

determined that certain one-time 

inspections are no longer necessary, 

certain compliance times may be 

extended, and an optional terminating 

action should be provided. This 

proposed AD would remove Model 

A340–500, and –600 series airplanes 

from the applicability, remove certain 

one-time inspections of the MLG bogie 

beams and the sliding piston subassembly; revise certain compliance 

times and provide, for certain airplanes, 

an optional terminating action for the 

repetitive actions. We are proposing this 

AD to detect and correct damage or 

corrosion under the bogie stop pad of 

both MLG bogie beams, which could 

result in a damaged bogie beam and 

consequent detachment of the beam 

from the airplane, or collapse of the 

MLG and departure of the airplane from 

the runway. 

DATES: We must receive comments on 

this proposed AD by April 15, 2016. 

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 NPRM, 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–2016– 

3984; 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–2016–3984; Directorate Identifier 

2014–NM–119–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 May 13, 2013, we issued AD 

2013–10–03, Amendment 39–17456 (78 

FR 31386, May 24, 2013). AD 2013–10– 

03 requires actions intended to address 

an unsafe condition on all Airbus Model 

A330–200, –200 Freighter, and –300 

series airplanes; and Model A340–200, 

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

(AD 2013–10–03 superseded AD 2010– 

02–10, Amendment 39–16181 (75 FR 

4477, January 28, 2010)). 

Since we issued AD 2013–10–03, 

Amendment 39–17456 (78 FR 31386, 

May 24, 2013), we have determined that 

certain one-time inspections are no 

longer necessary, certain compliance 

times may be extended, and an optional 

terminating action should be provided. 

The European Aviation Safety Agency 

(EASA), which is the Technical Agent 

for the Member States of the European 

Union, has issued EASA AD 2014– 

0120R1, dated August 31, 2015 (referred 

to after this as the Mandatory 

Continuing Airworthiness Information, 

or ‘‘the MCAI’’), to correct an unsafe 

condition for all Airbus Model A330– 

200, –200 Freighter, and –300 series 

airplanes; and Model A340–200, –300, 

–500, and –600 series airplanes. The 

MCAI states: 

During a scheduled maintenance 

inspection on the Main Landing Gear (MLG), 

the bogie stop pad was found deformed and 

cracked. Upon removal of the bogie stop pad 

for replacement, the bogie beam was also 

found cracked. 

The results of a laboratory investigation 

indicated that an overload event had 

occurred and no fatigue propagation of the 

crack was evident. 

A second bogie beam crack was 

subsequently found on another aeroplane, 

located under a bogie stop pad which only 

had superficial paint damage. 

This condition, if not detected and 

corrected, could lead to landing gear bogie 

detachment from the aeroplane, or landing 

gear collapse, or a runway excursion, 


asabaliauskas on DSK5VPTVN1PROD with PROPOSALS