Federal Register / Vol. 75, No. 37 / Thursday, February 25, 2010 / Proposed Rules 8551 

the compliance times specified, unless the 

actions have already been done. 

Actions 

(g) Unless already done, do the following 

actions. 

(1) At the later of the times specified in 

paragraph (g)(1)(i) and (g)(1)(ii) of this AD: 

Do a detailed inspection for cracks of the 

crossbeam on the nose landing gear FR15A 

web attachment fitting of rack 107VU, in 

accordance with the Accomplishment 

Instructions in the applicable service bulletin 

specified in Table 1 of this AD. 

(i) Before the accumulation of 6,600 total 

flight cycles. 

(ii) Within 2,300 flight cycles or 30 months 

after the effective date of this AD, whichever 

occurs first. 

(2) Thereafter, at intervals not to exceed 

2,300 flight cycles, repeat the inspection 

specified in paragraph (g)(1) of this AD. 

TABLE 1—SERVICE BULLETINS

Model Service Bulletin Date 

Airbus A300 series airplanes ................................ Airbus Mandatory Service Bulletin A300–53–0388, including Appendix 01.March 17, 2009. 

Airbus 300–600 series airplanes ........................... Airbus Mandatory Service Bulletin A300–53–6164, including Appendix 01.March 17, 2009. 

Airbus A310 series airplanes ................................ Airbus Mandatory Service Bulletin A310–53–2131, including Appendix 01.March 17, 2009. 

(3) If any crack is found during any 

inspection required by paragraphs (g)(1) and 

(g)(2) of this AD, before further flight contact 

Airbus for approved repair instructions and 

do the repair. 

(4) Submit an inspection report of the 

inspection required by paragraph (g)(1) of 

this AD to Airbus Customer Services 

Directorate, 1 Rond Point Maurice Bellonte, 

31707 Blagnac Cedex, France, telephone +33 

5 61 93 33 33; fax +33 5 61 93 28 06; e-mail: 

sb.reporting@airbus.com, at the applicable 

time specified in paragraph (g)(4)(i) or 

(g)(4)(ii) of this AD. The report must include 

the information specified on the inspection 

report sheet provided in Appendix 01 of the 

applicable service bulletin identified in Table 

1 of this AD. 

(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 done before 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 

(h) The following provisions also apply to 

this AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, International 

Branch, ANM–116, 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: Dan Rodina, 

Aerospace Engineer, International Branch, 

ANM–116, Transport Airplane Directorate, 

FAA, 1601 Lind Avenue, SW., Renton, 

Washington 98057–3356; telephone (425) 

227–2125; 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 

(i) Refer to MCAI European Aviation Safety 

Agency Airworthiness Directive 2009–0165, 

dated July 31, 2009; Airbus Mandatory 

Service Bulletin A300–53–0388, including 

Appendix 01, dated March 17, 2009; Airbus 

Mandatory Service Bulletin A300–53–6164, 

including Appendix 01, dated March 17, 

2009; and Airbus Mandatory Service Bulletin 

A310–53–2131, including Appendix 01, 

dated March 17, 2009; for related 

information. 

Issued in Renton, Washington, on February 

17, 2010. 

Stephen P. Boyd, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2010–3816 Filed 2–24–10; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2010–0172; Directorate 

Identifier 2009–NM–189–AD] 

RIN 2120–AA64 

Airworthiness Directives; Airbus Model 

A300, A300–600, and A310 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: 

In the past, some operators have reported 

difficulties to pressurise the hydraulic 

reservoirs, due to leakage of the Crissair 

reservoir air pressurisation check valves. 

* * * The leakage of the check valves was 

caused by an incorrect spring material. The 

affected Crissair check valves * * * were 

then replaced with improved check valves 

P/N [part number] 2S2794–1 * * *. 

More recently, similar issues were again 

reported on aeroplanes with Crissair check 

valves P/N 2S2794–1 installed. The 

investigations * * * have shown that a 

spring, mounted inside the valve, does not 

meet the Airbus type design specifications. 

This situation, if not corrected, can cause 

hydraulic system functional degradation, 

possibly resulting in reduced control of the 

aeroplane when combined with an air duct 

leak, air conditioning system contamination 

or, if installed, malfunction of the fire 

extinguishing system in the Class ‘C’ cargo 

compartment. 

* * * * * 

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 April 12, 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 


sroberts on DSKD5P82C1PROD with PROPOSALS
8552 Federal Register / Vol. 75, No. 37 / Thursday, February 25, 2010 / Proposed Rules 

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— 

EAW (Airworthiness Office), 1 Rond 

Point Maurice Bellonte, 31707 Blagnac 

Cedex, France; telephone +33 5 61 93 36 

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

account.airworth-eas@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 or 425–227–1152. 

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: Dan 

Rodina, Aerospace Engineer, 

International Branch, ANM–116, 

Transport Airplane Directorate, FAA, 

1601 Lind Avenue, SW., Renton, 

Washington 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–2010–0172; Directorate Identifier 

2009–NM–189–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 2009–0171, 

dated August 5, 2009 (referred to after 

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

condition for the specified products. 

The MCAI states: 

In the past, some operators have reported 

difficulties to pressurise the hydraulic 

reservoirs, due to leakage of the Crissair 

reservoir air pressurisation check valves. In 

some cases, the air conditioning system was 

contaminated with hydraulic mist. The 

leakage of the check valves was caused by an 

incorrect spring material. The affected 

Crissair check valves Part Number (P/N) 

2S2794 were then replaced with improved 

check valves P/N 2S2794–1 in accordance 

with Airbus Service Information Letter 29– 

020. 

More recently, similar issues were again 

reported on aeroplanes with Crissair check 

valves P/N 2S2794–1 installed. The 

investigations carried out on those check 

valves have shown that a spring, mounted 

inside the valve, does not meet the Airbus 

type design specifications. 

This situation, if not corrected, can cause 

hydraulic system functional degradation, 

possibly resulting in reduced control of the 

aeroplane when combined with an air duct 

leak, air conditioning system contamination 

or, if installed, malfunction of the fire 

extinguishing system in the Class ‘C’ cargo 

compartment. 

For the reasons described above, EASA AD 

2008–0166 was issued to require the 

inspection of the Crissair check valves P/N 

2S2794–1, to identify serial numbers (s/n) 

and the replacement of the affected ones with 

serviceable units. 

Later on, further investigation by the 

vendor Crissair revealed more suspect check 

valves P/N 2S2794–1. Based on this, it was 

concluded that EASA AD 2008–0166 did not 

adequately address the unsafe condition and 

also did not correctly identify the Functional 

Item Numbers (FIN) of the various aeroplane 

installations of the affected valves. 

Consequently, EASA AD Cancellation Notice 

No.: 2008–0166–CN was issued on 29 

October 2008 to cancel EASA AD 2008–0166. 

An updated list of suspect check valves 

with P/N 2S2794–1 has now been issued by 

Crissair Inc., the manufacturer. 

Consequently, this EASA AD requires the 

identification of the check valves by s/n and 

the replacement of the affected ones with 

serviceable units. 

You may obtain further information 

by examining the MCAI in the AD 

docket. 

Relevant Service Information 

Airbus has issued the following 

service bulletins: 

• Airbus Mandatory Service Bulletin 

A300–29–0124, Revision 02, including 

Appendices 1, 2, and 3, dated March 10, 

2009; 

• Airbus Mandatory Service Bulletin 

A300–29–6060, Revision 01, including 

Appendices 1, 2, and 3, dated March 10, 

2009; and 

• Airbus Mandatory Service Bulletin 

A310–29–2097, Revision 01, including 

Appendices 1, 2, and 3, dated March 19, 

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 206 products of U.S. 

registry. We also estimate that it would 


sroberts on DSKD5P82C1PROD with PROPOSALS
Federal Register / Vol. 75, No. 37 / Thursday, February 25, 2010 / Proposed Rules 8553 

take about 12 work-hours per product, 

depending on airplane configuration, 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 the 

proposed AD on U.S. operators to be 

$210,120, or $1,020 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: 

Airbus: Docket No. FAA–2010–0172; 

Directorate Identifier 2009–NM–189–AD. 

Comments Due Date 

(a) We must receive comments by April 12, 

2010. 

Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to Airbus Model A300 

B2–1A, B2–1C, B2K–3C, B2–203, B4–2C, B4– 

103, B4–203, B4–601, B4–603, B4–620, B4– 

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

and C4–605R Variant F airplanes; and Model 

A310–203, –204, –221, –222, –304, –322, 

–324, and –325 airplanes; certificated in any 

category, all certified models and all serial 

numbers on which any Crissair check valve 

part number 2S2794–1 is installed. 

Subject 

(d) Air Transport Association (ATA) of 

America Code 29: Hydraulic Power; and 26: 

Fire Protection. 

Reason 

(e) The mandatory continuing 

airworthiness information (MCAI) states: 

In the past, some operators have reported 

difficulties to pressurise the hydraulic 

reservoirs, due to leakage of the Crissair 

reservoir air pressurization check valves. In 

some cases, the air conditioning system was 

contaminated with hydraulic mist. The 

leakage of the check valves was caused by an 

incorrect spring material. The affected 

Crissair check valves Part Number (P/N) 

2S2794 were then replaced with improved 

check valves P/N 2S2794–1 in accordance 

with Airbus Service Information Letter 29– 

020. 

More recently, similar issues were again 

reported on aeroplanes with Crissair check 

valves P/N 2S2794–1 installed. The 

investigations carried out on those check 

valves have shown that a spring, mounted 

inside the valve, does not meet the Airbus 

type design specifications. 

This situation, if not corrected, can cause 

hydraulic system functional degradation, 

possibly resulting in reduced control of the 

aeroplane when combined with an air duct 

leak, air conditioning system contamination 

or, if installed, malfunction of the fire 

extinguishing system in the Class ‘C’ cargo 

compartment. 

For the reasons described above, EASA 

[European Aviation Safety Agency] AD 2008– 

0166 was issued to require the inspection of 

the Crissair check valves P/N 2S2794–1, to 

identify serial numbers (s/n) and the 

replacement of the affected ones with 

serviceable units. 

Later on, further investigation by the 

vendor Crissair revealed more suspect check 

valves P/N 2S2794–1. Based on this, it was 

concluded that EASA AD 2008–0166 did not 

adequately address the unsafe condition and 

also did not correctly identify the Functional 

Item Numbers (FIN) of the various aeroplane 

installations of the affected valves. 

Consequently, EASA AD Cancellation Notice 

No.: 2008–0166–CN was issued on 29 

October 2008 to cancel EASA AD 2008–0166. 

An updated list of suspect check valves 

with P/N 2S2794–1 has now been issued by 

Crissair Inc., the manufacturer. 

Consequently, this EASA AD requires the 

identification of the check valves by s/n and 

the replacement of the affected ones with 

serviceable units. 

Actions and Compliance 

(f) Unless already done, do the following 

actions. 

(1) At the applicable compliance time 

specified in Table 1 of this AD: For Crissair 

check valves, P/N 2S2794–1, identify the 

serial number using Appendix 1 of the 

applicable service bulletin identified in Table 

2 of this AD, in accordance with the 

Accomplishment Instructions in the 

applicable service bulletin identified in Table 

2 of this AD. Except as provided by 

paragraph (f)(2) of this AD, for any valve 

having a serial number listed in Appendix 1 

of the applicable service bulletin identified 

in Table 2 of this AD, before further flight, 

install a new or modified check valve in 

accordance with the applicable service 

bulletin identified in Table 2 of this AD. 

TABLE 1—AFFECTED CHECK VALVE INSTALLATION

Affected check valve installation, identified by FIN 

(functional item number) Compliance time 

(i) Airplanes having Hydraulic System with FIN 29/1388, FIN 29/2388 

and FIN 29/3388.

Within 4 months after the effective date of this AD. 

(ii) Cargo Compartment Fire Extinguishing System, equipped with Flow 

Metering System (A310 and A300–600 airplanes having ‘‘post-Airbus 

modification 06403’’ only) FIN 26/0203.

Within 4 months after the effective date of this AD. 


sroberts on DSKD5P82C1PROD with PROPOSALS
8554 Federal Register / Vol. 75, No. 37 / Thursday, February 25, 2010 / Proposed Rules 

TABLE 1—AFFECTED CHECK VALVE INSTALLATION—Continued 

Affected check valve installation, identified by FIN 

(functional item number) Compliance time 

(iii) Airplanes having Hydraulic System with FIN 29/1378, FIN 29/1382 

and FIN 29/1394.

Within 30 months after the effective date of this AD. 

(iv) Hydraulic System (A300 airplanes having configuration 01 

‘‘pre-Airbus modification 03079’’ only) FIN 29/1381.

Within 30 months after the effective date of this AD. 

(2) Check valves P/N 2S2794–1 marked 

with an ‘‘R’’ have already been modified in 

accordance with Crissair Service Bulletin 

20070407–29–1 and do not need to be 

replaced. Check valves with P/N 2S2794 are 

not affected and do not need to be replaced. 

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

person may install any Crissair check valve, 

P/N 2S2794–1, on any airplane unless it has 

a serial number other than those listed in 

Appendix 1 of the applicable service bulletin 

identified in Table 2 of this AD, or unless 

check valve P/N 2S2794–1 is marked with an 

‘‘R.’’ 

TABLE 2—SERVICE INFORMATION

Airbus model— Airbus Mandatory Service Bulletin— Revision— Dated— 

A300 airplanes ............................. A300–29–0124, including Appendices 1, 2, and 3 ........................... 02 March 10, 2009. 

A300–600 airplanes ..................... A300–29–6060, including Appendices 1, 2, and 3 ........................... 01 March 10, 2009. 

A310 airplanes ............................. A310–29–2097, including Appendices 1, 2, and 3 ........................... 01 March 19, 2009. 

(4) Submit an inspection report of the 

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

AD to Airbus Customer Services Directorate, 

1 Rond Point Maurice Bellonte, 31707 

Blagnac Cedex, France; telephone +33 5 61 

93 33 33; fax +33 5 61 93 42 51; e-mail: 

sb.reporting@airbus.com; at the applicable 

time specified in paragraph (f)(4)(i) or 

(f)(4)(ii) of this AD. The report must include 

the information specified on the inspection 

report sheet provided in the applicable 

service bulletin identified in Table 2 of this 

AD. 

(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 done before 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: 

Although the MCAI states not to install the 

part identified in paragraph (f)(3) of this AD 

after accomplishing the actions specified in 

paragraph (f)(1) of this AD, this AD prohibits 

installation of the part as of the effective date 

of this AD. 

Other FAA AD Provisions 

(g) 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: Dan Rodina, 

Aerospace Engineer, International Branch, 

ANM–116, Transport Airplane Directorate, 

FAA, 1601 Lind Avenue, SW., Renton, 

Washington 98057–3356; telephone (425) 

227–2125; 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 

(h) Refer to MCAI EASA Airworthiness 

Directive 2009–0171, dated August 5, 2009; 

and the service bulletins identified in Table 

2 of this AD; for related information. 

Issued in Renton, Washington, on February 

17, 2010. 

Stephen P. Boyd, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2010–3817 Filed 2–24–10; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2010–0132; Directorate 

Identifier 2009–NM–096–AD] 

RIN 2120–AA64 

Airworthiness Directives; The Boeing 

Company Model 747–100, –200B, and 

–200F Series Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: The FAA proposes to 

supersede an existing airworthiness 

directive (AD) that applies to certain 

Model 747–100, 747–200B, and –200F 

series airplanes. The existing AD 

currently requires inspections to detect 

cracking in the upper row of fasteners 

holes of the skin lap joints in the 

fuselage lower lobe, and repair, if 

necessary. This proposed AD would 

reduce the maximum interval of the 

post-modification inspections. This 

proposed AD results from reports of 

fatigue cracking on modified airplanes. 

We are proposing this AD to detect and 

correct fatigue cracking in the 

longitudinal lap joints of the fuselage 

lower lobe, which could lead to the 

rapid decompression of the airplane and 

the inability of the structure to carry 

fail-safe loads. 

DATES: We must receive comments on 

this proposed AD by April 12, 2010. 

ADDRESSES: You may send comments by 

any of the following methods: 


sroberts on DSKD5P82C1PROD with PROPOSALS