Federal Register / Vol. 79, No. 136 / Wednesday, July 16, 2014 / Proposed Rules 41459 

Applicability 

As discussed above, these special 

conditions are applicable to the Models 

BD–500–1A10 and BD–500–1A11 series 

airplanes. Should Bombardier 

Aerospace apply at a later date for a 

change to the type certificate to include 

another model incorporating the same 

novel or unusual design feature, the 

special conditions would apply to that 

model as well. 

Conclusion 

This action affects only certain novel 

or unusual design features on two 

model series of airplanes. It is not a rule 

of general applicability. 

List of Subjects in 14 CFR Part 25 

Aircraft, Aviation safety, Reporting 

and recordkeeping requirements. 

The authority citation for these 

special conditions is as follows: 

Authority: 49 U.S.C. 106(g), 40113, 44701, 

44702, 44704. 

The Proposed Special Conditions 

Accordingly, the Federal Aviation 

Administration (FAA) proposes the 

following special conditions as part of 

the type certification basis for 

Bombardier Aerospace Models BD–500– 

1A10 and BD–500–1A11 series 

airplanes. 

Composite Wing and Fuel Tank PostCrash Fire Survivability 

1. The wing fuel tank structure must 

withstand an external fuel-fed pool fire 

for a minimum of 5 minutes. 

2. The integrity of the wing fuel tank 

structure must be demonstrated at: 

• Minimum fuel load, not less than 

reserve fuel level; 

• Maximum fuel load equal to the 

maximum range fuel quantity; and 

• Any other critical fuel loads. 

3. The demonstration must consider 

fuel tank flammability, burn-through 

resistance, wing structural strength 

retention properties, and auto-ignition 

threats from localized heating of 

composite structure, fasteners, or any 

other feature that may produce an 

ignition source during a ground fire 

event for the required time duration. 

Issued in Renton, Washington, on June 19, 

2014. 

Michael Kaszycki, 

Acting Manager, Transport Airplane 

Directorate. 

[FR Doc. 2014–16645 Filed 7–15–14; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2014–0448; Directorate 

Identifier 2013–NM–055–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 all 

Airbus Model A300 series airplanes; 

Airbus Model A300 B4–600, B4–600R, 

and F4–600R series airplanes, and 

Model A300 C4–605R Variant F 

airplanes (collectively called Model 

A300–600 series airplanes); and Airbus 

Model A310 series airplanes. This 

proposed AD was prompted by a report 

of early ruptures on the levers of the 

nose landing gear (NLG) sequence valve. 

This proposed AD would require a onetime inspection for damage of the 

landing gear sequence valve levers and 

pin shearing indicating areas on the 

NLG and the main landing gears 

(MLGs); and depending on findings, 

replacing the sequence valve and lever, 

or doing a one-time inspection to detect 

interference between control rods and 

sequence valves and corrective actions 

if necessary. We are proposing this AD 

to detect and correct interference 

between a landing gear leg and door, 

which could result in failure of that 

landing gear to extend and could 

damage the airplane and injure 

occupants. 

DATES: We must receive comments on 

this proposed AD by September 2, 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—EAW, 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 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– 

0448; 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: Dan 

Rodina, Aerospace Engineer, 

International Branch, ANM–116, 

Transport Airplane Directorate, FAA, 

1601 Lind Avenue SW., Renton, WA 

98057–3356; telephone 425–227–2125; 

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–2014–0448; Directorate Identifier 

2013–NM–055–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 2013–0058, 

dated March 11, 2013 (referred to after 


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this as the Mandatory Continuing 

Airworthiness Information, or ‘‘the 

MCAI’’), to correct an unsafe condition 

for all Airbus Model A300 series 

airplanes; Airbus Model A300 B4–600, 

B4–600R, and F4–600R series airplanes, 

and Model A300 C4–605R Variant F 

airplanes (collectively called Model 

A300–600 series airplanes); and Airbus 

Model A310 series airplanes. The MCAI 

states: 

Operators have reported five cases of early 

ruptures on levers of the nose landing gear 

(NLG) sequence valve. 

Analysis showed that these fatigue 

ruptures were due to an incorrect adjustment 

of the mechanical links. As the design of the 

main landing gear (MLG) sequence valve 

lever is similar, there is sufficient reason to 

assume that these parts are similarly affected 

by fatigue. 

This condition, if not detected and 

corrected, could lead to interference between 

landing gear leg and door and consequent 

failure of the landing gear to extend, possibly 

resulting in damage to the aeroplane and 

injury to occupants. 

For the reasons described above, this 

[EASA] AD requires a one-time inspection of 

the sequence valve control lever [for damage, 

which could include cracking or 

deformation], of the adjustment of the control 

rod between doors and landing gear sequence 

valve and depending on inspections results, 

accomplishment of applicable corrective 

actions. 

The corrective actions include adjusting 

the control rod between the door and 

the sequence valves; adjusting 

mechanical linkages; and replacing/

installing a serviceable valve and lever. 

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– 

0448. 

Relevant Service Information 

Airbus has issued Service Bulletins: 

• A300–32–0464, dated July 17, 2012 

(for Model A300 airplanes); 

• A300–32–6110, dated July 17, 2012 

(for Model A300–600 airplanes); and 

• A310–32–2146, dated July 17, 2012 

(for Model A310 airplanes). 

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 another NPRM, 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 other NPRM, 

Directorate Identifier 2012–NM–101–AD 

(78 FR 78285, December 26, 2013), 

stated the following: ‘‘The proposed 

wording, being specific to repairs, 

eliminates the interpretation that Airbus 

messages are acceptable for approving 

minor deviations (corrective actions) 

needed during accomplishment of an 

AD mandated Airbus service bulletin.’’ 

This comment has made the FAA 

aware that some operators have 

misunderstood or misinterpreted the 

Airworthy Product paragraph to allow 

the owner/operator to use messages 

provided by the manufacturer as 

approval of deviations during the 

accomplishment of an AD-mandated 

action. The Airworthy Product 

paragraph does not approve messages or 

other information provided by the 

manufacturer for deviations to the 

requirements of the AD-mandated 

actions. The Airworthy Product 

paragraph only addresses the 

requirement to contact the manufacturer 

for corrective actions for the identified 

unsafe condition and does not cover 

deviations from other AD requirements. 

However, deviations to AD-required 

actions are addressed in 14 CFR 39.17, 

and anyone may request the approval 

for an alternative method of compliance 

to the AD-required actions using the 

procedures found in 14 CFR 39.19. 

To address this misunderstanding and 

misinterpretation of the Airworthy 

Product paragraph, we have changed 

that paragraph and retitled it 

‘‘Contacting the Manufacturer.’’ This 

paragraph now clarifies that for any 

requirement in this 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 128 airplanes of U.S. registry. 


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Federal Register / Vol. 79, No. 136 / Wednesday, July 16, 2014 / Proposed Rules 41461 

We also estimate that it would take 

about 4 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 $43,520, or $340 per product. 

In addition, we estimate that any 

necessary follow-on actions would take 

up to 9 work-hours and require parts 

costing up to $42,000, for a cost of 

$42,765 per product. We have no way 

of determining the number of aircraft 

that might need these actions. 

Authority for This Rulemaking 

Title 49 of the United States Code 

specifies the FAA’s authority to issue 

rules on aviation safety. Subtitle I, 

section 106, describes the authority of 

the FAA Administrator. ‘‘Subtitle VII: 

Aviation Programs,’’ describes in more 

detail the scope of the Agency’s 

authority. 

We are issuing this rulemaking under 

the authority described in ‘‘Subtitle VII, 

Part A, Subpart III, Section 44701: 

General requirements.’’ Under that 

section, Congress charges the FAA with 

promoting safe flight of civil aircraft in 

air commerce by prescribing regulations 

for practices, methods, and procedures 

the Administrator finds necessary for 

safety in air commerce. This regulation 

is within the scope of that authority 

because it addresses an unsafe condition 

that is likely to exist or develop on 

products identified in this rulemaking 

action. 

Regulatory Findings 

We determined that this 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. Amend § 39.13 by adding the 

following new airworthiness directive 

(AD): 

Airbus: Docket No. FAA–2014–0448; 

Directorate Identifier 2013–NM–055–AD. 

(a) Comments Due Date 

We must receive comments by September 

2, 2014. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to all Airbus airplanes 

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

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

(1) Airbus Model A300 B2–1A, B2–1C, 

B2K–3C, B2–203, B4–2C, B4–103, and B4– 

203 airplanes. 

(2) Airbus Model A300 B4–601, B4–603, 

B4–620, B4–622, B4–605R, B4–622R, F4– 

605R, F4–622R, and C4–605R Variant F 

airplanes. 

(3) Airbus Model A310–203, –204, –221, 

–222, –304, –322, –324, and –325 airplanes. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 32, Landing Gear. 

(e) Reason 

This AD was prompted by a report of early 

ruptures on the levers of the nose landing 

gear (NLG) sequence valve. We are issuing 

this AD to detect and correct interference 

between a landing gear leg and door, which 

could result in failure of that landing gear to 

extend, and could damage the airplane and 

injure occupants. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Service Information 

Do the actions required by paragraph (h) of 

this AD in accordance with the applicable 

service information identified in paragraphs 

(g)(1) through (g)(3) of this AD. 

(1) For Model A300 airplanes: Airbus 

Service Bulletin A300–32–0464, dated July 

17, 2012. 

(2) For Model A300–600 airplanes: Airbus 

Service Bulletin A300–32–6110, dated July 

17, 2012. 

(3) For Model A310 airplanes: Airbus 

Service Bulletin A310–32–2146, dated July 

17, 2012. 

(h) Inspections and Corrective Actions 

Within 4,000 flight cycles, 6,000 flight 

hours, or 30 months after the effective date 

of this AD, whichever occurs first: Do a 

detailed inspection of each sequence valve 

lever and pin shearing indicating area on the 

nose landing gear and main landing gears for 

any damage, in accordance with the 

Accomplishment Instructions of the 

applicable service information identified in 

paragraph (g) of this AD. Do the actions 

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

this AD in accordance with the 

Accomplishment Instructions of the 

applicable service information identified in 

paragraph (g) of this AD. 

(1) If damage is found, before further flight, 

replace the affected sequence valve and its 

lever with a serviceable sequence valve and 

lever. No further action is required by 

paragraph (h) of this AD for that replaced 

valve and lever. 

(2) If no damage is found, within the 

compliance time required by paragraph (h) of 

this AD, do a detailed inspection to detect 

interference between the landing gear door 

control rod and the landing gear sequence 

valve, and do all applicable corrective 

actions. Do all applicable corrective actions 

before further flight. No further action is 

required by paragraph (h) of this AD. 

(3) For the purposes of this AD, a detailed 

inspection is: An intensive examination of a 

specific item, installation, or assembly to 

detect damage, failure, or irregularity. 

Available lighting is normally supplemented 

with a direct source of good lighting at an 

intensity deemed appropriate. Inspection 

aids such as mirror, magnifying lenses, etc., 

may be necessary. Surface cleaning and 

elaborate procedures may be required. 

(i) Parts Installation Limitation 

As of the effective date of this AD, no 

person may install on any airplane a landing 

gear sequence valve, unless that valve has 

been inspected and corrected, as applicable, 

in accordance with the requirements of 

paragraph (h) of this AD. 

(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: 

Dan Rodina, Aerospace Engineer, 

International Branch, ANM–116, Transport 

Airplane Directorate, FAA, 1601 Lind 

Avenue SW., Renton, WA 98057–3356; 

telephone 425–227–2125; fax 425–227–1149. 

Information may be emailed to: 9-ANM-116- 


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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 

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. 

(k) Related Information 

(1) Refer to Mandatory Continuing 

Airworthiness Information (MCAI) European 

Aviation Safety Agency (EASA) 

Airworthiness Directive 2013–0058, dated 

March 11, 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 it in Docket No. 

FAA–2014–0448. 

(2) For service information identified in 

this AD, contact Airbus SAS, Airworthiness 

Office—EAW, 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 July 3, 

2014. 

Dionne Palermo, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2014–16690 Filed 7–15–14; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2014–0472; Directorate 

Identifier 2013–SW–040–AD] 

RIN 2120–AA64 

Airworthiness Directives; Agusta S.p.A 

Helicopters (Type Certificate Currently 

Held by AgustaWestland S.p.A.) 

(Agusta) 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to adopt a new 

airworthiness directive (AD) for certain 

Agusta Model A109E, A109K2, A119, 

and AW119 MKII helicopters. This 

proposed AD was prompted by a report 

of a crack that was found on a Gleason 

crown. This proposed AD would require 

repetitively performing a magnetic 

particle inspection of the Gleason crown 

for a crack. We are proposing this AD 

to detect a crack, which could cause 

damage to or loss of the main rotor drive 

and subsequent loss of control of the 

helicopter. 

DATES: We must receive comments on 

this proposed AD by September 2, 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: 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 proposed AD, contact 

AgustaWestland, Product Support 

Engineering, Via del Gregge, 100, 21015 

Lonate Pozzolo (VA) Italy, ATTN: 

Maurizio D’Angelo; telephone 39–0331– 

664757; fax 39–0331–664680; or at 

http://www.agustawestland.com/

technical-bullettins. You may review the 

referenced service information at the 

FAA, Office of the Regional Counsel, 

Southwest Region, 2601 Meacham 

Blvd., Room 663, Fort Worth, Texas 

76137. 

Examining the AD Docket 

You may examine the AD docket on 

the Internet at http://

www.regulations.gov; 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 

European Aviation Safety Agency 

(EASA) 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: Rao 

Edupuganti, Aviation Safety Engineer, 

Regulations and Policy Group, 

Rotorcraft Directorate, FAA, 2601 

Meacham Blvd., Fort Worth, Texas 

76137; telephone (817) 222–5110; email 

rao.edupuganti@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– 

2014–0472; Directorate Identifier 2013– 

SW–040–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 

EASA, which is the Technical Agent 

for the Member States of the European 

Union, has issued EASA AD No. 2013– 

0118, dated June 3, 2013, to correct an 

unsafe condition for Agusta Model 

A109K2, A109E, A119, and AW119MKII 

helicopters. EASA advises that during 

an overhaul of an A119 main 

transmission, part number (P/N) 109– 

0400–05–103, a crack on the Gleason 

crown, P/N 109–0403–07–103, was 

found. EASA further states that an 

investigation by Agusta revealed that 

the crack originated from the bottom of 

one of the 40 threaded holes in the 

Gleason crown, and that this partnumbered Gleason crown is also 

installed on Model A109 helicopters. 

EASA states that this condition, if not 

corrected, could cause damage to or loss 

of the main rotor drive and loss of 

control of the helicopter. To correct this 

unsafe condition, EASA AD No. 2013– 

0118 requires repetitive magnetic 

particle inspections of the Gleason 

crown and, if there is a crack, replacing 

the Gleason crown with a different partnumbered Gleason crown. EASA AD 

No. 2013–0118 also prohibits installing 

a Gleason crown, P/N 109–0403–07– 

103, or a Gleason crown assembly, P/N 

109–0401–27–101 or P/N 109–0401–27– 

109, on any helicopter, as Gleason 

crown, P/N 109–0403–07–103, is a 

component of these assemblies. 

Relevant Service Information 

We reviewed Agusta Bollettino 

Tecnico (BT) No. 109EP–128 for Model 

A109E helicopters, Agusta BT No. 

109K–57 for Model A109K2 helicopters, 

and Agusta BT No. 119–058 for Model 


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