11006 Federal Register / Vol. 74, No. 49 / Monday, March 16, 2009 / Rules and Regulations 

under the criteria of the Regulatory 

Flexibility Act. 

We prepared an economic evaluation 

of the estimated costs to comply with 

this AD and placed it in the AD docket. 

List of Subjects in 14 CFR Part 39 

Air transportation, Aircraft, Aviation 

safety, Incorporation by reference, 

Safety. 

Adoption of the Amendment 

■ Accordingly, under the authority 

delegated to me by the Administrator, 

the FAA amends 14 CFR part 39 as 

follows: 

PART 39—AIRWORTHINESS 

DIRECTIVES 

■ 1. The authority citation for part 39 

continues to read as follows: 

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

§ 39.13 [Amended] 

■ 2. The FAA amends § 39.13 by adding 

the following new AD: 

2009–06–01 Eurocopter France: 

Amendment 39–15837. Docket No. 

FAA–2009–0195; Directorate Identifier 

2007–SW–34–AD. 

Effective Date 

(a) This airworthiness directive (AD) 

becomes effective on March 31, 2009. 

Other Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to Model EC 155B and 

EC155B1 helicopters with a serial number (S/ 

N) less than 6763, and with optional 

equipment OP 45C07 (OP 45C07), installed, 

certificated in any category. OP 45C07 is the 

helicopter provision kit (electrical and 

structural mount modifications) used to 

support installation and operation of a hoist. 

(1) To determine if your helicopter has OP 

45C07 installed, review aircraft 

documentation, which should state if OP 

45C07 equipment is installed, or 

(2) Perform a physical inspection for the 

existence of the 24 Delta hoist electrical 

female connector (MIL–C–5015 type 

connector), which is installed, just forward of 

the right-hand engine cowling and just below 

the right engine inlet. Figures 1 and 6 of 

Eurocopter Emergency Alert Service Bulletin 

No. 25A085, dated June 1, 2007 (ASB), depict 

where the connector is located. 

Reason 

(d) The mandatory continuing 

airworthiness information (MCAI) states that 

‘‘the Airworthiness Directive (AD) is 

prompted by the discovery of a short circuit 

evidence in hoist connector ‘‘24 Delta’’ even 

though the hoist was removed from the 

rotorcraft. The short circuit generated 

sufficient heat to ignite the paint on the 

cooler support cowling near the hoist cut-off 

connector ‘‘24 Delta.’’ This condition, if not 

corrected, could result in a fire in this area 

which could propagate to surrounding 

zones.’’ This AD requires actions that are 

intended to address this unsafe condition. 

Actions and Compliance 

(e) Within 7 days, unless already 

accomplished, do the following: 

(1) Determine the orientation of the fixed 

connector ‘‘24 Delta’’ and if the large contacts 

are not oriented ‘‘aft,’’ re-orient the fixed 

connector so that they are facing ‘‘aft’’ by 

following the Accomplishment Instructions, 

paragraphs 2.B.1. and 2.B.2.a., of the ASB. 

(2) Immediately after each hoist removal 

until the electrical bonding braid for the 

fixed hoist connector ‘‘24 Delta’’ is installed, 

disconnect the hoist power cable by 

following the Accomplishment Instructions, 

paragraph 2.B.2.b., of the ASB. 

(f) Within 1 month, install an electrical 

bonding braid for connector ‘‘24 Delta’’ by 

following the Accomplishment Instructions, 

paragraph 2.B.2.c., of the ASB. 

(g) Factory-implemented modification 

MOD 0745C82 is acceptable terminating 

action for the requirements of this AD. 

Differences Between This AD and the MCAI 

(h) We have used a compliance time of 1 

month rather than 3 months because of the 

serious consequences of an undetected short 

circuit and potential aircraft fire. 

Other Information 

(i) Alternative Methods of Compliance 

(AMOCs): The Manager, Safety Management 

Group, FAA, ATTN: George Schwab, 

Aerospace Engineer, Rotorcraft Directorate, 

Regulations and Policy Group, Fort Worth, 

Texas 76193–0111, telephone (817) 222– 

5114, fax (817) 222–5961, has the authority 

to approve AMOCs for this AD, if requested 

using the procedures found in 14 CFR 39.19. 

Related Information 

(j) Mandatory Continuing Airworthiness 

Information (MCAI) Emergency 

Airworthiness Directive No. 2007–0159–E, 

dated June 6, 2007, contains related 

information. 

Air Transport Association of America (ATA) 

Tracking Code 

(k) ATA Code 25: 2500–Hoist box; 1420– 

Hoist cut-off connector. 

Material Incorporated by Reference 

(l) You must use the specified portions of 

Eurocopter Emergency Alert Service Bulletin 

No. 25A085, dated June 1, 2007, to do the 

actions required. 

(1) The Director of the Federal Register 

approved the incorporation by reference of 

this service information under 5 U.S.C. 

552(a) and 1 CFR part 51. 

(2) For service information identified in 

this AD, contact American Eurocopter 

Corporation, 2701 Forum Drive, Grand 

Prairie, TX 75053–4005, telephone (972) 

641–3460, fax (972) 641–3527, or at http:// 

www.eurocopter.com. 

(3) You may review copies at the FAA, 

Office of the Regional Counsel, Southwest 

Region, 2601 Meacham Blvd., Room 663, Fort 

Worth, Texas, or at the National Archives 

and Records Administration (NARA). For 

information on the availability of this 

material at NARA, call (202) 741–6030, or go 

to: http://www.archives.gov/federal-register/ 

cfr/ibr-locations.html. 

Issued in Fort Worth, Texas on February 

19, 2009. 

Scott A. Horn, 

Acting Manager, Rotorcraft Directorate, 

Aircraft Certification Service. 

[FR Doc. E9–4953 Filed 3–13–09; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2009–0215; Directorate 

Identifier 2007–NM–278–AD; Amendment 

39–15850; AD 2009–06–13] 

RIN 2120–AA64 

Airworthiness Directives; Airbus Model 

A321–131 Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule; request for 

comments. 

SUMMARY: The FAA is adopting a new 

airworthiness directive (AD) for certain 

Airbus Model A321–131 airplanes. This 

AD requires repetitive ultrasonic 

inspections to detect cracks in the wing 

inner rear spars at the attachment holes 

of the Main Landing Gear (MLG) 

forward pintle fitting, the actuator 

cylinder anchorage fitting, and rib 5 

fitting; and repair of the sealant or repair 

of any crack. This AD results from a 

finding that certain A321–131 airplanes 

may not reach the design life goal due 

to differences in thickness of the inner 

rear spars and that fatigue cracks may 

develop on inner rear spars starting 

from the fastener holes for the 

attachment of gear rib 5, the forward 

pintle fitting, and the actuating cylinder 

anchorage on these airplanes. We are 

issuing this AD to detect and correct 

such fatigue cracks, which could result 

in reduced structural integrity of the 

airplane. 

DATES: This AD becomes effective 

March 31, 2009. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in the AD 

as of March 31, 2009. 

We must receive comments on this 

AD by April 15, 2009. 

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. 

Federal Register / Vol. 74, No. 49 / Monday, March 16, 2009 / Rules and Regulations 11007 

• 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 20590, between 9 a.m. 

and 5 p.m., Monday through Friday, 

except Federal holidays. 

For service information identified in 

this AD, contact Airbus, Airworthiness 

Office—EAS, 1 Rond Point Maurice 

Bellonte, 31707 Blagnac Cedex, France; 

fax +33 5 61 93 44 51; e-mail: 

account.airworth-eas@airbus.com; 

Internet http://www.airbus.com. 

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 AD, the regulatory 

evaluation, any comments received, and 

other information. The street address for 

the Docket 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: Tim 

Dulin, Aerospace Engineer, 

International Branch, ANM–116, 

Transport Airplane Directorate, FAA, 

1601 Lind Avenue, SW., Renton, 

Washington 98057–4056; telephone 

425–227–2141; fax 425–227–1320. 

SUPPLEMENTARY INFORMATION:

Discussion 

The European Aviation Safety Agency 

(EASA), which is the Technical Agent 

for the Member States of the European 

Community, notified us that an unsafe 

condition may exist on certain Airbus 

Model A321–131 airplanes. EASA 

advises that two airplanes, manufacturer 

serial number (MSN) 364 and 385, may 

not reach the design life goal due to 

differences in thickness of the inner rear 

spars and that fatigue cracks may 

develop on inner rear spars starting 

from the fastener holes for the 

attachment of gear rib 5, the forward 

pintle fitting, and the actuating cylinder 

anchorage on these airplanes. This 

condition, if not detected and corrected, 

could result in reduced structural 

integrity of the airplane. 

Other Relevant Rulemaking 

We previously issued airworthiness 

directive (AD) 2006–04–11 R1, 

amendment 39–14628 (71 FR 32807, 

June 7, 2006), applicable to certain 

Airbus Model A321–111, –112, and 

–131 airplanes; MSNs 364 and 385 were 

specifically excluded. That AD requires 

repetitive inspections to detect fatigue 

cracking in the area surrounding certain 

attachment holes of the forward pintle 

fittings of the main landing gear and the 

actuating cylinder anchorage fittings on 

the inner rear spars; and repair, if 

necessary. That AD also provides for 

optional terminating action for the 

repetitive inspections, adds inspections 

of three additional mounting holes, and 

revises the inspection thresholds 

required by an earlier AD. 

Relevant Service Information 

Airbus has issued Service Bulletin 

A320–57–1126, dated August 8, 2003. 

The service bulletin describes 

procedures for doing repetitive 

ultrasonic inspections to detect cracks 

in the wing inner rear spars at the 

attachment holes of the MLG forward 

pintle fitting, the actuator cylinder 

anchorage fitting, and rib 5 fitting; and 

repairing of the sealant if no cracks are 

found or contacting Airbus for repair 

instructions if any cracks are found. 

The EASA mandated the service 

information and issued airworthiness 

directive 2007–0162, dated June 12, 

2007 (referred to after this as ‘‘the 

MCAI’’), to ensure the continued 

airworthiness of these airplanes in the 

European Union. The EASA 

airworthiness directive also includes 

requirements for other Model A321 

airplanes; however, FAA AD 2006–04– 

11 R1, described previously, adequately 

addresses these other requirements (as 

specified in paragraph 1 of the MCAI). 

FAA’s Determination and Requirements 

of This 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. 

Therefore, we are issuing this AD to 

detect and correct fatigue cracks on the 

wing inner rear spars. This AD requires 

accomplishing the actions specified in 

the service information described 

previously, except as discussed under 

‘‘Difference Between the AD and Service 

Bulletin.’’ 

Difference Between the AD and Service 

Bulletin 

The service bulletin specifies to 

contact the manufacturer for 

instructions on how to repair certain 

conditions, but this AD requires 

repairing those conditions using a 

method approved by the FAA or EASA 

(or its delegated agent). In light of the 

type of repair that is required to address 

the unsafe condition, and consistent 

with existing bilateral airworthiness 

agreements, we have determined that, 

for this AD, a repair approved by the 

FAA or EASA (or its delegated agent) 

would be acceptable for compliance 

with this AD. 

Costs of Compliance 

None of the airplanes affected by this 

action are on the U.S. Register. All 

airplanes affected by this AD are 

currently operated by non-U.S. 

operators under foreign registry; 

therefore, they are not directly affected 

by this AD action. However, we 

consider this AD necessary to ensure 

that the unsafe condition is addressed if 

any affected airplane is imported and 

placed on the U.S. Register in the future. 

The following table provides the 

estimated costs to comply with this AD 

for any affected airplane that might be 

imported and placed on the U.S. 

Register in the future. 

ESTIMATED COSTS

Action Work hours Average labor 

rate per hour Parts cost Cost per airplane 

Inspection, per inspection cycle ......................... 46 $80 None ............................. $3,680 per inspection cycle. 

11008 Federal Register / Vol. 74, No. 49 / Monday, March 16, 2009 / Rules and Regulations 

FAA’s Determination of the Effective 

Date 

No airplane affected by this AD is 

currently on the U.S. Register. 

Therefore, providing notice and 

opportunity for public comment is 

unnecessary before this AD is issued, 

and this AD may be made effective in 

less than 30 days after it is published in 

the Federal Register. 

Comments Invited 

This AD is a final rule that involves 

requirements affecting flight safety, and 

we did not provide you with notice and 

an opportunity to provide your 

comments before it becomes effective. 

However, we invite you to send any 

written data, views, or arguments about 

this AD. Send your comments to an 

address listed under the ADDRESSES

section. Include ‘‘Docket No. FAA– 

2009–0215; Directorate Identifier 2007– 

NM–278–AD’’ at the beginning of your 

comments. We specifically invite 

comments on the overall regulatory, 

economic, environmental, and energy 

aspects of this AD. We will consider all 

comments received by the closing date 

and may amend this 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 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 have determined that this AD will 

not have federalism implications under 

Executive Order 13132. This AD will 

not have a substantial direct effect on 

the States, on the relationship between 

the national government and the States, 

or on the distribution of power and 

responsibilities among the various 

levels of government. 

For the reasons discussed above, I 

certify that the 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); and 

3. 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. 

We prepared a regulatory evaluation 

of the estimated costs to comply with 

this AD and placed it in the AD docket. 

See the ADDRESSES section for a location 

to examine the regulatory evaluation. 

List of Subjects in 14 CFR Part 39 

Air transportation, Aircraft, Aviation 

safety, Incorporation by reference, 

Safety. 

Adoption of the Amendment 

■ Accordingly, under the authority 

delegated to me by the Administrator, 

the FAA amends 14 CFR part 39 as 

follows: 

PART 39—AIRWORTHINESS 

DIRECTIVES 

■ 1. The authority citation for part 39 

continues to read as follows: 

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

§ 39.13 [Amended] 

■ 2. The Federal Aviation 

Administration (FAA) amends § 39.13 

by adding the following new 

airworthiness directive (AD): 

2009–06–13 Airbus: Amendment 39–15850. 

Docket No. FAA–2009–0215; Directorate 

Identifier 2007–NM–278–AD. 

Effective Date 

(a) This AD becomes effective March 31, 

2009. 

Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to Airbus Model A321– 

131 airplanes, certificated in any category, 

manufacturer serial numbers (MSNs) 364 and 

385. 

Subject 

(d) Air Transport Association (ATA) of 

America Code 57: Wings. 

Unsafe Condition 

(e) This AD results from a finding that 

certain A321–131 airplanes may not reach 

the design life goal due to differences in 

thickness of the inner rear spars and that 

fatigue cracks may develop on inner rear 

spars starting from the fastener holes for the 

attachment of gear rib 5, the forward pintle 

fitting, and the actuating cylinder anchorage 

on these airplanes. We are issuing this AD to 

detect and correct fatigue cracks on the wing 

inner rear spars, which could result in 

reduced structural integrity of the airplane. 

Compliance 

(f) You are responsible for having the 

actions required by this AD performed within 

the compliance times specified, unless the 

actions have already been done. 

Repetitive Inspections 

(g) At the later of the times specified in 

paragraphs (g)(1) and (g)(2) of this AD, do an 

ultrasonic inspection to detect cracks of the 

left-hand and right-hand wing inner rear 

spars at the attachment holes of the main 

landing gear (MLG) forward pintle fitting, the 

actuator cylinder anchorage fitting, and gear 

rib 5 fitting, in accordance with the 

Accomplishment Instructions of Airbus 

Service Bulletin A320–57–1126, dated 

August 8, 2003. Repeat the inspection 

thereafter at intervals not to exceed 3,600 

flight cycles or 5,600 flight hours, whichever 

occurs first. 

(1) Before the accumulation of 24,000 total 

flight cycles or 39,400 total flight hours from 

first flight, whichever occurs first. 

(2) Within 6 months after the effective date 

of this AD. 

Repair 

(h) If no crack is detected during any 

inspection required by paragraph (g) of this 

AD, before further flight, repair the sealant in 

the inspected areas in accordance with the 

Accomplishment Instructions of Airbus 

Service Bulletin A320–57–1126, dated 

August 8, 2003. 

(i) If any crack is detected during any 

inspection required by paragraph (g) of this 

AD, before further flight, repair the crack 

using a method approved by either the 

Manager, International Branch, ANM–116, 

Transport Airplane Directorate, FAA; or the 

European Aviation Safety Agency (EASA) (or 

its delegated agent). 

Alternative Methods of Compliance 

(AMOCs) 

(j) The Manager, International Branch, 

FAA, has the authority to approve AMOCs 

for this AD, if requested using the procedures 

found in 14 CFR 39.19. Send information to 

ATTN: Tim Dulin, Aerospace Engineer, 

International Branch, ANM–116, Transport 

Airplane Directorate, FAA, 1601 Lind 

Avenue, SW., Renton, Washington 98057– 

4056; telephone 425–227–2141; fax 425–227– 

1320. Before using any approved AMOC on 

any airplane to which the AMOC applies, 

notify your principal maintenance inspector 

(PMI) or principal avionics inspector (PAI), 

as appropriate, or lacking a principal 

inspector, your local Flight Standards District 

Office. 

Related Information 

(k) EASA airworthiness directive 2007– 

0162, dated June 12, 2007, also addresses the 

subject of this AD. 

Federal Register / Vol. 74, No. 49 / Monday, March 16, 2009 / Rules and Regulations 11009 

Material Incorporated by Reference 

(l) You must use Airbus Service Bulletin 

A320–57–1126, dated August 8, 2003, to do 

the actions required by this AD, unless the 

AD specifies otherwise. 

(1) The Director of the Federal Register 

approved the incorporation by reference of 

this service information under 5 U.S.C. 

552(a) and 1 CFR part 51. 

(2) For service information identified in 

this AD, contact Airbus, Airworthiness 

Office—EAS, 1 Rond Point Maurice Bellonte, 

31707 Blagnac Cedex, France; fax +33 5 61 

93 44 51; e-mail: account.airwortheas@airbus.com; Internet http:// 

www.airbus.com. 

(3) You may review copies of the service 

information that is incorporated by reference 

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 or 425–227–1152. 

(4) You may also review copies of the 

service information at the National Archives 

and Records Administration (NARA). For 

information on the availability of this 

material at NARA, call 202–741–6030, or go 

to: http://www.archives.gov/federal_register/ 

code_of_federal_regulations/ 

ibr_locations.html. 

Issued in Renton, Washington, on February 

27, 2009. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. E9–5009 Filed 3–13–09; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2009–0170; Directorate 

Identifier 2008–SW–45–AD; Amendment 39– 

15843; AD 2009–06–07] 

RIN 2120–AA64 

Airworthiness Directives; Agusta 

S.p.A. Model AB139 and AW139 

Helicopters 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule; request for 

comments. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for Agusta 

S.p.A. Model AB139 and AW139 

helicopters. This AD results from 

mandatory continuing airworthiness 

information (MCAI) issued by the 

European Aviation Safety Agency 

(EASA), which is the Technical Agent 

for the Member States of the European 

Community. The MCAI states: 

‘‘Operators had reported a number of 

occurrences of in-flight losses of cockpit 

door windows, both left and right side. 

This condition, if not corrected, could 

result in damage to critical 

components.’’ The actions specified by 

this AD are intended to require that 

cockpit door windows (windows) be 

replaced with re-designed windows to 

prevent a window from separating from 

the helicopter, contacting the tailboom 

or tail rotor, resulting in loss of control 

of the helicopter. 

DATES: This AD becomes effective on 

March 31, 2009. 

The incorporation by reference of 

certain publications is approved by the 

Director of the Federal Register as of 

March 31, 2009. 

We must receive comments on this 

AD by May 15, 2009. 

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 your 

comments electronically. 

• 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 20590, between 9 a.m. 

and 5 p.m., Monday through Friday, 

except Federal holidays. 

You may get the service information 

identified in this AD from Agusta, 

Product Support Italy, Via per 

Tornavento, 15 21019 Somma 

Lombardo, Varese Italy, telephone 39 

(0331) 711111, fax 39 (0331) 711397, or 

at http://customersupport.agusta.com/ 

technical_advice.php. 

Examining the Docket: You may 

examine the AD docket on the Internet 

at http://www.regulations.gov or in 

person at the Docket Operations office 

between 9 a.m. and 5 p.m., Monday 

through Friday, except Federal holidays. 

The AD docket contains this AD, the 

economic evaluation, any comments 

received, and other information. The 

street address for the Docket Operations 

office (telephone (800) 647–5527) is 

stated in the ADDRESSES section of this 

AD. Comments will be available in the 

AD docket shortly after receipt. 

FOR FURTHER INFORMATION CONTACT: 

Sharon Miles, Aviation Safety Engineer, 

FAA, Rotorcraft Directorate, Regulations 

and Guidance Group, Fort Worth, Texas 

76193–0111, telephone (817) 222–5122, 

fax (817) 222–5961. 

SUPPLEMENTARY INFORMATION: 

Discussion 

The EASA, which is the Technical 

Agent for the Member States of the 

European Community, has issued EASA 

AD No. 2008–0108, dated June 5, 2008, 

to correct an unsafe condition for Model 

AB139 and AW139 helicopters. 

Previously, EASA issued AD 2007– 

0142, which required a dimensional 

check and, if necessary, repairing the 

cockpit door installation and replacing 

the window seal. After the issuance of 

AD 2007–0142, cases of cracks on 

windows leading to loss of part of the 

window were reported on cockpit doors 

on which actions required by AD 2007– 

0142 were applied. Therefore, EASA 

issued AD 2008–0011, which 

superseded AD 2007–0142 and included 

the same requirements, but also 

required reinforcing the windows in the 

area where cracks had reportedly 

developed. Additional cases of in-flight 

breakage of windows have been 

reported concerning cockpit doors on 

which the actions required by AD 2008– 

0011 were applied. Further 

investigation showed that cracks had 

originated in a different area of the 

windows than with the previous cases, 

suggesting a different route to failure. 

You may obtain further information 

by examining the MCAI and any related 

service information in the AD docket. 

Related Service Information 

Agusta S.p.A. has issued Bollettino 

Tecnico No. 139–129, dated June 3, 

2008 (BT 139–129), which describes 

replacing the left-hand side window 

with a window, part number (P/N) 

3P5211A10152A1, and right-hand side 

window with a window, P/N 

3P5211A48131A1, as well as installing 

an additional strap to allow immediate 

jettison in an emergency and installing 

a new external emergency exit placard, 

P/N 212–072–636–109. The actions 

described in the MCAI are intended to 

correct the same unsafe condition as 

that identified in the service 

information. 

FAA’s Evaluation and Unsafe Condition 

Determination 

These helicopters have been approved 

by the aviation authority of Italy, and 

are approved for operation in the United 

States. Pursuant to our bilateral 

agreement with Italy, their Technical 

Agent, EASA, has notified us of the 

unsafe condition described in the MCAI. 

We are issuing this AD because we 

evaluated all information provided by 

EASA and determined the unsafe 

condition exists and is likely to exist or 

develop on other helicopters of these 

same type designs.