16696 Federal Register / Vol. 75, No. 63 / Friday, April 2, 2010 / Proposed Rules 

Seer2/Seer3 Customer Services; fax +33 (0)5 

61 93 28 73; e-mail 

region1.structurerepairsupport@airbus.com, 

region2.structurerepairsupport@airbus.com, 

or 

region3.structurerepairsupport@airbus.com. 

For negative findings, submit the report to 

Nicolas Seynaeve, Sees1, Customer Services; 

telephone +33 (0)5 61 93 34 38; fax +33 (0)5 

61 93 36 14; e-mail 

nicolas.seynaeve@airbus.com. 

(1) For any inspection done on or after the 

effective date of this AD: Submit the report 

within 30 days after the inspection. 

(2) For any inspection done before the 

effective date of this AD: Submit the report 

within 30 days after the effective date of this 

AD. 

(k) All rudders that have passed the 

inspection specified in paragraphs (g)(1), 

(g)(2), (g)(3), (g)(4), (h)(1), (h)(2), (h)(3), and 

(h)(4) of this AD, before the effective date of 

this AD in accordance with Airbus AOT 

A320–55A1038, dated April 22, 2009; AOT 

A320–55A1038, Revision 01, dated June 10, 

2009; or Airbus Technical Disposition TD/ 

K4/S2/27051/2009, Issue B, dated February 

25, 2009; are compliant with this AD for the 

areas inspected; except additional areas 

requiring inspection, as defined in Section 0, 

‘‘Reason for Revision,’’ of Airbus AOT A320– 

55A1038, Revision 02, dated September 28, 

2009, must be inspected as specified in 

paragraph (g) or (h) of this AD. For all areas, 

the repetitive inspections required by 

paragraph (g) or (h) of this AD remain 

applicable. 

(l) After the effective date of this AD, no 

rudder listed in Table 1 of this AD may be 

installed on any airplane, unless the rudder 

is in compliance with the requirements of 

this AD. 

FAA AD Differences 

Note 2: This AD differs from the MCAI 

and/or service information as follows: No 

differences. 

Other FAA AD Provisions 

(m) 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. 

Send information to ATTN: Tim Dulin, 

Aerospace Engineer, International Branch, 

ANM–116, Transport Airplane Directorate, 

FAA, 1601 Lind Avenue, SW., Renton, 

Washington 98057–3356; telephone (425) 

227–2141; fax (425) 227–1149. 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. 

The AMOC approval letter must specifically 

reference this AD. 

(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 

(44 U.S.C. 3501 et seq.), the Office of 

Management and Budget (OMB) has 

approved the information collection 

requirements and has assigned OMB Control 

Number 2120–0056. 

Related Information 

(n) Refer to MCAI European Aviation 

Safety Agency Airworthiness Directive 2009– 

0141, dated July 2, 2009; Airbus All 

Operators Telex A320–55A1038, Revision 02, 

dated September 28, 2009; and Airbus 

Technical Disposition TD/K4/S2/27086/ 

2009, Issue E, dated September 17, 2009; for 

related information. 

Issued in Renton, Washington, on March 

25, 2010. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2010–7461 Filed 4–1–10; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2010–0278; Directorate 

Identifier 2009–NM–255–AD] 

RIN 2120–AA64 

Airworthiness Directives; Airbus Model 

A330–223, –321, –322, and –323 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to adopt a new 

airworthiness directive (AD) for the 

products listed above. This proposed 

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 accomplishment of 

Damage Tolerant—Airworthiness 

Limitation Item task 712106–01–01 from 

A330 ALS Part 2, an A330 operator 

found a Fluorescent Penetrant 

Inspection (FPI) indication in the head 

of the shank filet radius in one of the 

Pratt & Whitney (PW) forward (FWD) 

engine mount pylon bolts. Dual-bolt 

fractures could lead to inability for 

mount assembly to sustain loads which 

may lead to an engine mount failure and 

consequently to engine separation from 

the aeroplane during flight, which 

would constitute an unsafe condition. 

The proposed AD would require 

actions that are intended to address the 

unsafe condition described in the MCAI. 

DATES: We must receive comments on 

this proposed AD by May 17, 2010. 

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. 

For service information identified in 

this proposed AD, contact Airbus SAS— 

Airworthiness Office—EAL, 1 Rond 

Point Maurice Bellonte, 31707 Blagnac 

Cedex, France; telephone +33 5 61 93 36 

96; fax +33 5 61 93 45 80; e-mail 

airworthiness.A330–A340@airbus.com; 

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

may review copies of the 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. 

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 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, 

Washington 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 


wwoods2 on DSK1DXX6B1PROD with PROPOSALS_PART 1
Federal Register / Vol. 75, No. 63 / Friday, April 2, 2010 / Proposed Rules 16697 

this proposed AD. Send your comments 

to an address listed under the 

ADDRESSES section. Include ‘‘Docket No. 

FAA–2010–0278; Directorate Identifier 

2009–NM–255–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 have lengthened the 30-day 

comment period for proposed ADs that 

address MCAI originated by aviation 

authorities of other countries to provide 

adequate time for interested parties to 

submit comments. The comment period 

for these proposed ADs is now typically 

45 days, which is consistent with the 

comment period for domestic transport 

ADs. 

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 2009–0240, 

dated November 5, 2009 (referred to 

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

unsafe condition for the specified 

products. The MCAI states: 

During accomplishment of Damage 

Tolerant—Airworthiness Limitation Item task 

712106–01–01 from A330 ALS Part 2, an 

A330 operator found a Fluorescent Penetrant 

Inspection (FPI) indication in the head of the 

shank filet radius in one of the Pratt & 

Whitney (PW) forward (FWD) engine mount 

pylon bolts. 

Investigation has confirmed that this FPI 

indication was due to a quality 

manufacturing process issue which led to a 

bolt non-conformance and is also applicable 

to aft ward (AFT) mount pylon bolts. 

Dual-bolt fractures could lead to inability 

for mount assembly to sustain loads which 

may lead to an engine mount failure and 

consequently to engine separation from the 

aeroplane during flight, which would 

constitute an unsafe condition. 

This AD requires a one time detailed visual 

inspection of the FWD and AFT mount pylon 

bolts on all A330 aeroplanes fitted with PW 

engines (8 bolts per engine) and replacement 

of any affected bolt. 

You may obtain further information by 

examining the MCAI in the AD docket. 

Relevant Service Information 

Airbus has issued Mandatory Service 

Bulletin A330–71–3020, including 

Appendix 1, dated June 10, 2009. 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. 

Differences Between This 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 proposed 

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 

proposed AD. 

Costs of Compliance 

Based on the service information, we 

estimate that this proposed AD would 

affect about 41 products of U.S. registry. 

We also estimate that it would take 

about 7 work-hours per product to 

comply with the basic requirements of 

this proposed AD. The average labor 

rate is $85 per work-hour. Required 

parts would cost about $16,672 per 

product. Where the service information 

lists required parts costs that are 

covered under warranty, we have 

assumed that there will be no charge for 

these costs. As we do not control 

warranty coverage for affected parties, 

some parties may incur costs higher 

than estimated here. Based on these 

figures, we estimate the cost of the 

proposed AD on U.S. operators to be 

$707,947, or $17,267 per product. 

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); 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 proposed 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. 

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 AD: 


wwoods2 on DSK1DXX6B1PROD with PROPOSALS_PART 1
16698 Federal Register / Vol. 75, No. 63 / Friday, April 2, 2010 / Proposed Rules 

Airbus: Docket No. FAA–2010–0278; 

Directorate Identifier 2009–NM–255–AD. 

Comments Due Date 

(a) We must receive comments by May 17, 

2010. 

Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to Airbus Model A330– 

223, –321, –322, and –323 airplanes; 

certificated in any category; all manufacturer 

serial numbers. 

Subject 

(d) Air Transport Association (ATA) of 

America Code 71: Powerplant. 

Reason 

(e) The mandatory continuing 

airworthiness information (MCAI) states: 

During accomplishment of Damage 

Tolerant—Airworthiness Limitation Item task 

712106–01–01 from A330 ALS Part 2, an 

A330 operator found a Fluorescent Penetrant 

Inspection (FPI) indication in the head of the 

shank filet radius in one of the Pratt & 

Whitney (PW) forward (FWD) engine mount 

pylon bolts. 

Investigation has confirmed that this FPI 

indication was due to a quality 

manufacturing process issue which led to a 

bolt non-conformance and is also applicable 

to aft ward (AFT) mount pylon bolts. 

Dual-bolt fractures could lead to inability 

for mount assembly to sustain loads which 

may lead to an engine mount failure and 

consequently to engine separation from the 

aeroplane during flight, which would 

constitute an unsafe condition. 

This AD requires a one time detailed visual 

inspection of the FWD and AFT mount pylon 

bolts on all A330 aeroplanes fitted with PW 

engines (8 bolts per engine) and replacement 

of any affected bolt. 

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. 

Actions 

(g) Do a detailed inspection to determine 

the part number, serial number, and lot 

number of the forward and aft mount pylon 

bolts on both engines, in accordance with the 

Accomplishment Instructions of Airbus 

Mandatory Service Bulletin A330–71–3020, 

dated June 10, 2009. Inspect at the later of 

the times specified in paragraphs (g)(1) and 

(g)(2) of this AD. 

(1) Before the accumulation of 8,000 total 

flight cycles or 24,000 total flight hours, 

whichever occurs first. 

(2) Within 24 months after the effective 

date of this AD. 

(h) If the identified part number, serial 

number, or lot number corresponds to a 

suspect bolt number identified in Pratt & 

Whitney Service Bulletin PW4G–100–71–35, 

dated March 14, 2008, before further flight 

remove the affected bolt and replace with a 

serviceable bolt, in accordance with the 

Accomplishment Instructions of Airbus 

Mandatory Service Bulletin A330–71–3020, 

dated June 10, 2009. 

(i) If the bolt part number, serial number, 

or lot number is unreadable, before further 

flight remove the affected bolt and replace 

with a serviceable bolt, in accordance with 

the Accomplishment Instructions of Airbus 

Mandatory Service Bulletin A330–71–3020, 

dated June 10, 2009. 

(j) As of the effective date of this AD, no 

person may install any forward or aft mount 

pylon bolt on any airplane, unless this bolt 

has been identified as a non-suspect bolt, in 

accordance with the Accomplishment 

Instructions of Airbus Mandatory Service 

Bulletin A330–71–3020, dated June 10, 2009. 

(k) Although Airbus Mandatory Service 

Bulletin A330–71–3020, dated June 10, 2009, 

specifies to submit certain information to the 

manufacturer, this AD does not include that 

requirement. 

FAA AD Differences 

Note 1: This AD differs from the MCAI 

and/or service information as follows: 

Although the MCAI or service information 

tells you to submit information to the 

manufacturer, paragraph (k) of this AD 

specifies that such submittal is not required. 

Other FAA AD Provisions 

(l) 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. 

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 

principal maintenance inspector (PMI) or 

principal avionics inspector (PAI), as 

appropriate, or lacking a principal inspector, 

your local Flight Standards District Office. 

The AMOC approval letter must specifically 

reference this AD. 

(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. 

Related Information 

(m) Refer to MCAI European Aviation 

Safety Agency (EASA) Airworthiness 

Directive 2009–0240, dated November 5, 

2009; and Airbus Mandatory Service Bulletin 

A330–71–3020, dated June 10, 2009; for 

related information. 

Issued in Renton, Washington, on March 

25, 2010. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2010–7460 Filed 4–1–10; 8:45 am] 

BILLING CODE 4910–13–P 

OFFICE OF THE DIRECTOR OF 

NATIONAL INTELLIGENCE 

32 CFR Part 1701 

Privacy Act of 1974: Implementation 

AGENCY: Office of the Director of 

National Intelligence. 

ACTION: Proposed rulemaking. 

SUMMARY: The Office of the Director of 

National Intelligence (ODNI) proposes 

to exempt fourteen (14) new systems of 

records from subsections (c)(3); (d)(1), 

(2), (3), (4); (e)(1) and (e)(4)(G), (H), (I); 

and (f) of the Privacy Act, pursuant to 

5 U.S.C. 552a(k). 

DATES: Submit comments on or before 

May 12, 2010. 

ADDRESSES: You may submit comments 

by any of the following methods: 

Federal eRulemaking Portal: http:// 

www.regulations.gov. 

Mail: Director, Information 

Management, Office of the Director of 

National Intelligence, Washington DC, 

20511. 

FOR FURTHER INFORMATION CONTACT: Mr. 

John F. Hackett, Director, Information 

Management, (703) 275–2215. 

SUPPLEMENTARY INFORMATION: In 

compliance with the Privacy Act, 5 

U.S.C. 552a(e)(4), the ODNI describes in 

the notice section of today’s Federal 

Register the following fourteen (14) new 

systems of records: Manuscript, 

Presentation and Resume Review 

Records; Executive Secretary Action 

Management System Records; Public 

Affairs Office Records; Office of 

Legislative Affairs Records; ODNI Guest 

Speaker Records; Office of General 

Counsel Records; Analytic Resources 

Catalog; Intelligence Community 

Customer Registry; EEO and Diversity 

Office Records; Office of Protocol 

Records; IC Security Clearance and 

Access Approval Repository; Security 

Clearance Reform Research Records; 

Civil Liberties and Privacy Office 

Complaint Records, and National 

Intelligence Council Consultation 

Records. The ODNI has previously 

established a rule that it will preserve 

the exempt status of records it receives 

when the reason for the exemption 

remains valid (73 FR 166531, March 28, 

2008). 


wwoods2 on DSK1DXX6B1PROD with PROPOSALS_PART 1