25404 Federal Register / Vol. 74, No. 101 / Thursday, May 28, 2009 / Rules and Regulations 

BLADE PART NUMBER (P/N)— 

Continued 

117–151441V002, 117–151441V003 

117–151451, 117–151451V001 

117–151451V002, 117–151451V003 

117–151461, 117–151461V001 

Reason 

(d) Redesigned blades have become 

available that are not fitted with lead balance 

weights. Only a blade equipped with a lead 

balance weight may contain the unsafe 

condition. This AD retains the requirements 

of the current AD but limits the applicability 

to those part-numbered blades that are fitted 

with lead balance weights. The actions are 

intended to detect the blades fitted with lead 

balance weights that could move and cause 

severe vibrations leading to blade failure and 

subsequent loss of control of the helicopter. 

Actions and Compliance 

(e) Required as indicated: 

(1) Within 5 hours time-in-service (TIS), 

unless already done, and thereafter at 

intervals not to exceed 50 hours TIS, visually 

inspect the upper and lower surfaces of each 

affected main rotor blade (blade) in the area 

of the outboard lead balance weight in the 

marked inspection area for bulging. 

(i) If a marked inspection area is not 

visible, mark the area using a water-resistant 

and indelible marking pencil and then 

inspect the upper and lower surfaces of each 

blade in the area of the outboard lead balance 

weight for bulging. 

Note: For guidance, the current MBB– 

BK117 Maintenance Manual at Figure 14–5A 

contains the dimensions and placement of 

the inspection area. 

(ii) If bulging exceeds 1 millimeter (mm) 

(0.040 inch) in height, before further flight, 

remove the blade and replace it with an 

airworthy blade that is not listed in the 

applicability of this AD. 

(2) Replacing the affected blade with an 

airworthy blade that is not listed in the 

applicability of this AD is terminating action 

for the requirements of this AD. 

Differences Between This AD and the MCAI 

AD 

(f) We refer to flight hours as hours TIS. We 

retained the compliance time from the 

current AD and the Eurocopter ASB, dated 

August 18, 1994, and did not include the 

option of accumulating 1,800 flight hours 

since the first flight as stated in the MCAI. 

We do not incorporate ASB, Revision 3, 

damage inspection. We do not require that 

you contact ECD for instructions for 

corrective action. This AD requires that you 

contact the FAA for an Alternate Method of 

Compliance. 

Other Information 

(g) Alternative Methods of Compliance 

(AMOCs): The Manager, Safety Management 

Group, FAA, ATTN: Sharon Miles, Aviation 

Safety Engineer, Rotorcraft Directorate, 

Regulations and Guidance Group, Fort 

Worth, Texas 76193–0111, telephone (817) 

222–5122, 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 

(h) European Aviation Safety Agency 

(EASA) AD No. 2008–0156, dated August 19, 

2008, and Eurocopter Alert Service Bulletin 

MBB–BK117 No. ASB–MBB–BK117–10–108, 

Revision 3, dated August 7, 2008, contains 

related information. 

Air Transport Association of America (ATA) 

Tracking Code 

(i) ATA Code No. 6210 Main Rotor Blades. 

Issued in Fort Worth, Texas, on May 7, 

2009. 

Mark R. Schilling, 

Acting Manager, Rotorcraft Directorate, 

Aircraft Certification Service. 

[FR Doc. E9–12320 Filed 5–27–09; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2009–0479; Directorate 

Identifier 2009–NM–006–AD; Amendment 

39–15918; AD 2009–11–08] 

RIN 2120–AA64 

Airworthiness Directives; Airbus Model 

A330–202, –223, –243, –301, –322, and 

–342 Airplanes 

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 the 

products listed above. This AD results 

from mandatory continuing 

airworthiness information (MCAI) 

originated by an aviation authority of 

another country to identify and correct 

an unsafe condition on an aviation 

product. The MCAI describes the unsafe 

condition as: 

During the A330 and A340 aircraft fatigue 

test, cracks appeared on the right and left 

sides between the crossing area of the keel 

angle fitting and the front spar of the Centre 

Wing Box (CWB). Several modifications have 

been introduced in the fleet in the area of 

frame [FR] 40 keel angle assembly in order 

to prevent these cracks. However the new 

design has caused interference between one 

fastener and the keel angle which was 

corrected by further local reprofiling of the 

keel angle horizontal flange. Analysis shows 

that without an inspection of this reprofiled 

area, the structural integrity of the area is 

impacted, which constitutes an unsafe 

condition. 

* * * * * 

This AD requires actions that are 

intended to address the unsafe 

condition described in the MCAI. 

DATES: This AD becomes effective June 

12, 2009. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in the AD 

as of June 12, 2009. 

We must receive comments on this 

AD by June 29, 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. 

• 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 

W12–40, 1200 New Jersey Avenue, SE., 

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

p.m., Monday through Friday, except 

Federal holidays. 

Examining the AD 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 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, 

Washington 98057–3356; telephone 

(425) 227–1138; fax (425) 227–1149. 

SUPPLEMENTARY INFORMATION: 

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 2008–0213, 

dated December 8, 2008 (referred to 

after this as ‘‘the MCAI’’), to correct an 

unsafe condition for the specified 

products. The MCAI states: 

During the A330 and A340 aircraft fatigue 

test, cracks appeared on the right and left 

sides between the crossing area of the keel 

angle fitting and the front spar of the Centre 

Wing Box (CWB). Several modifications have 

Federal Register / Vol. 74, No. 101 / Thursday, May 28, 2009 / Rules and Regulations 25405 

been introduced in the fleet in the area of 

frame [FR] 40 keel angle assembly in order 

to prevent these cracks. However the new 

design has caused interference between one 

fastener and the keel angle which was 

corrected by further local reprofiling of the 

keel angle horizontal flange. Analysis shows 

that without an inspection of this reprofiled 

area, the structural integrity of the area is 

impacted, which constitutes an unsafe 

condition. 

In order to maintain the structural integrity 

of the aircraft, this Airworthiness Directive 

(AD) requires a repetitive special detailed 

inspection [high frequency eddy current to 

detect cracking] on the horizontal flange of 

the keel beam in the area of first fastener hole 

aft of FR40, and in case of cracks to repair 

accordingly. 

You may obtain further information 

by examining the MCAI in the AD 

docket. 

Relevant Service Information 

Airbus has issued Mandatory Service 

Bulletin A330–53–3151, Revision 01, 

including Appendix 1, dated September 

25, 2008. 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 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 issuing this 

AD because we evaluated all pertinent 

information and determined the unsafe 

condition exists and is likely to exist or 

develop on other products of the same 

type design. 

There are no products of this type 

currently registered in the United States. 

However, this rule is necessary to 

ensure that the described unsafe 

condition is addressed if any of these 

products are placed on the U.S. Register 

in the future. 

Differences Between the AD and the 

MCAI or Service Information 

We have reviewed the MCAI and 

related service information and, in 

general, agree with their substance. But 

we might have found it necessary to use 

different words from those in the MCAI 

to ensure the AD is clear for U.S. 

operators and is enforceable. In making 

these changes, we do not intend to differ 

substantively from the information 

provided in the MCAI and related 

service information. 

We might also have required different 

actions in this AD from those in the 

MCAI in order to follow FAA policies. 

Any such differences are highlighted in 

a NOTE within the AD. 

FAA’s Determination of the Effective 

Date 

Since there are currently no domestic 

operators of this product, notice and 

opportunity for public comment before 

issuing this AD are unnecessary. 

Comments Invited 

This AD is a final rule that involves 

requirements affecting flight safety, and 

we did not precede it by notice and 

opportunity for public comment. We 

invite you to send any written relevant 

data, views, or arguments about this AD. 

Send your comments to an address 

listed under the ADDRESSES section. 

Include ‘‘Docket No. FAA–2009–0479; 

Directorate Identifier 2009–NM–006– 

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 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 this AD: 

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. 

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: 

2009–11–08 Airbus: Amendment 39–15918. 

Docket No. FAA–2009–0479; Directorate 

Identifier 2009–NM–006–AD. 

Effective Date 

(a) This airworthiness directive (AD) 

becomes effective June 12, 2009. 

Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to Airbus Model A330– 

202, –223, –243, –301, –322 and –342 

airplanes; certificated in any category; serial 

numbers 0177, 0181, 0183, 0184, 0188, 0189, 

0191, 0195, 0198, 0200, 0203, 0205, 0206, 

0209, 0211, 0219, 0222, 0223, 0224, 0226, 

0229, 0230, 0231, 0232, 0234, 0238, 0240, 

0241, 0244, 0247, 0248, 0249, 0250, 0251, 

0253, 0254, and 0255. 

Subject 

(d) Air Transport Association (ATA) of 

America Code 53: Fuselage. 

Reason 

(e) The mandatory continued airworthiness 

information (MCAI) states: 

During the A330 and A340 aircraft fatigue 

test, cracks appeared on the right and left 

25406 Federal Register / Vol. 74, No. 101 / Thursday, May 28, 2009 / Rules and Regulations 

sides between the crossing area of the keel 

angle fitting and the front spar of the Centre 

Wing Box (CWB). Several modifications have 

been introduced in the fleet in the area of 

frame [FR] 40 keel angle assembly in order 

to prevent these cracks. However the new 

design has caused interference between one 

fastener and the keel angle which was 

corrected by further local reprofiling of the 

keel angle horizontal flange. Analysis shows 

that without an inspection of this reprofiled 

area, the structural integrity of the area is 

impacted, which constitutes an unsafe 

condition. 

In order to maintain the structural integrity 

of the aircraft, this Airworthiness Directive 

(AD) requires a repetitive special detailed 

inspection [high frequency eddy current to 

detect cracking] on the horizontal flange of 

the keel beam in the area of first fastener hole 

aft of FR40 and in case of cracks to repair 

accordingly. 

Actions and Compliance 

(f) Unless already done, do the following 

actions. 

(1) Within 90 days after the effective date 

of this AD, or at the applicable time specified 

in paragraph (f)(1)(i) or (f)(1)(ii) of this AD, 

whichever occurs later, perform a special 

detailed (high frequency eddy current) 

inspection to detect cracking of the keel beam 

fitting horizontal flange edge at FR40 on the 

left-hand and right-hand sides of the 

fuselage, in accordance with the instructions 

of Airbus Mandatory Service Bulletin A330– 

53–3151, Revision 01, dated September 25, 

2008. 

(i) For Model A330–301, –322, and –342 

airplanes: Before accumulating 14,500 total 

flight cycles or 37,000 total flight hours from 

the first flight of the airplane, whichever 

occurs first. 

(ii) For Model A330–202, –223, and –243 

airplanes: Before accumulating 14,100 total 

flight cycles or 70,600 total flight hours from 

the first flight of the airplane, whichever 

occurs first. 

(2) If no crack is detected during the 

inspection required by paragraph (f)(1) of this 

AD, repeat the inspection specified in 

paragraph (f)(1) of this AD thereafter at 

intervals not to exceed the times specified in 

paragraph (f)(2)(i) or (f)(2)(ii) of this AD, as 

applicable. 

(i) For Model A330–301, –322, and –342 

airplanes: 6,230 flight cycles or 15,900 flight 

hours, whichever occurs first. 

(ii) For Model A330–202, –223, and –243 

airplanes: 6,060 flight cycles or 30,300 flight 

hours, whichever occurs first. 

(3) If any crack is found during any 

inspection required by this AD, before further 

flight, contact Airbus and follow their 

corrective actions. 

(4) Airplanes that have already been 

inspected prior to the effective date of this 

AD in accordance with the instructions of 

Airbus Service Bulletin A330–53–3151, 

dated December 6, 2005, are compliant with 

the requirements of paragraph (f)(1) of this 

AD (initial inspection). However, after the 

effective date of this AD, the repetitive 

inspections must be continued in accordance 

with the instructions of Airbus Mandatory 

Service Bulletin A330–53–3151, Revision 01, 

dated September 25, 2008, as specified in 

paragraph (f)(1) of this AD. 

(5) At the applicable time specified in 

paragraph (f)(5)(i) or (f)(5)(ii) of this AD, 

submit a report of the results (both positive 

and negative) of the inspection required by 

paragraph (f)(1) of this AD, in accordance 

with Airbus Mandatory Service Bulletin 

A330–53–3151, Revision 01, dated 

September 25, 2008. Send the report to 

Airbus SAS—Customer Services Directorate, 

1 Rond Point Maurice Bellonte, 31707 

Blagnac Cedex, France; Attention SEDCC1 

Technical Data and Documentation Services, 

fax +33 5 61 93 28 06, e-mail 

sb.reporting@airbus.com. 

(i) If the inspection was done on or after 

the effective date of this AD: Submit the 

report within 30 days after the inspection. 

(ii) If the inspection was accomplished 

prior to the effective date of this AD: Submit 

the report within 30 days after the effective 

date of this AD. 

FAA AD Differences 

Note 1: This AD differs from the MCAI 

and/or service information as follows: No 

differences. 

Other FAA AD Provisions 

(g) The following provisions also apply to 

this AD: 

(1) Alternative Methods of Compliance 

(AMOCs): 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: Vladimir Ulyanov, 

Aerospace Engineer, International Branch, 

ANM–116, Transport Airplane Directorate, 

FAA, 1601 Lind Avenue, SW., Renton, 

Washington 98057–3356; telephone (425) 

227–1138; fax (425) 227–1149. Before using 

any approved AMOC on any airplane to 

which the AMOC applies, notify your 

appropriate principal maintenance inspector 

(PMI) or principal avionics inspector (PAI), 

as appropriate, or lacking a principal 

inspector, your local Flight Standards District 

Office. 

(2) Airworthy Product: For any requirement 

in this AD to obtain corrective actions from 

a manufacturer or other source, use these 

actions if they are FAA-approved. Corrective 

actions are considered FAA-approved if they 

are approved by the State of Design Authority 

(or their delegated agent). You are required 

to assure the product is airworthy before it 

is returned to service. 

(3) Reporting Requirements: For any 

reporting requirement in this AD, under the 

provisions of the Paperwork Reduction Act, 

the Office of Management and Budget (OMB) 

has approved the information collection 

requirements and has assigned OMB Control 

Number 2120–0056. 

Related Information 

(h) Refer to (MCAI) European Aviation 

Safety Agency (EASA) Airworthiness 

Directive 2008–0213, dated December 8, 

2008; and Airbus Mandatory Service Bulletin 

A330–53–3151, Revision 01, dated 

September 25, 2008; for related information. 

Material Incorporated by Reference 

(i) You must use Airbus Mandatory Service 

Bulletin A330–53–3151, Revision 01, 

including Appendix 1, dated September 25, 

2008, 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 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, e-mail 

airworthiness.A330-A340@airbus.com; 

Internet http://www.airbus.com. 

(3) You may review copies of the 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 or 425–227–1152. 

(4) You may also review copies of the 

service information that is incorporated by 

reference 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 May 15, 

2009. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. E9–12113 Filed 5–27–09; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 97 

[Docket No. 30667 Amdt. No 3222] 

Standard Instrument Approach 

Procedures, and Takeoff Minimums 

and Obstacle Departure Procedures; 

Miscellaneous Amendments 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: This establishes, amends, 

suspends, or revokes Standard 

Instrument Approach Procedures 

(SIAPs) and associated Takeoff 

Minimums and Obstacle Departure 

Procedures for operations at certain 

airports. These regulatory actions are 

needed because of the adoption of new 

or revised criteria, or because of changes 

occurring in the National Airspace 

System, such as the commissioning of 

new navigational facilities, adding new 

obstacles, or changing air traffic 

requirements. These changes are 

designed to provide safe and efficient