22514 Federal Register / Vol. 75, No. 82 / Thursday, April 29, 2010 / Rules and Regulations 

1C12–43 that has been replaced for any 

reason on or before doing the action in 

paragraph (f)(1) of this AD, within 150 hours 

time-in-service after June 3, 2010 (the 

effective date of this AD) do a functional 

inspection of the main and standby fuel 

pumps for leakage following steps 1 through 

14 of the Accomplishment Instructions of 

PIAGGIO AERO INDUSTRIES S.p.A Service 

Bulletin (Mandatory) N.: 80–0278, dated July 

15, 2009. 

(3) If any leakage is found during the 

inspection required in paragraph (f)(2) of this 

AD, before further flight, replace the fuel 

pump with a serviceable unit following the 

Accomplishment Instructions in PIAGGIO 

AERO INDUSTRIES S.p.A Service Bulletin 

(Mandatory) N.: 80–0278, dated July 15, 

2009. For the purpose of this AD, a 

serviceable fuel pump is a pump where no 

leakage is found during the functional 

inspection as instructed in the 

Accomplishment Instructions of PIAGGIO 

AERO INDUSTRIES S.p.A Service Bulletin 

(Mandatory) N.: 80–0278, dated July 15, 

2009. 

FAA AD Differences 

Note: 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, Standards Office, 

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: Sarjapur Nagarajan, Aerospace 

Engineer, FAA, Small Airplane Directorate, 

901 Locust, Room 301, Kansas City, Missouri 

64106; telephone: (816) 329–4145; fax: (816) 

329–4090. Before using any approved AMOC 

on any airplane to which the AMOC applies, 

notify your appropriate principal inspector 

(PI) in the FAA Flight Standards District 

Office (FSDO), or lacking a PI, your local 

FSDO. 

(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 AD No.: 2009– 

0228, dated October 26, 2009; and PIAGGIO 

AERO INDUSTRIES S.p.A Service Bulletin 

(Mandatory) N.: 80–0278, dated July 15, 

2009, for related information. 

Material Incorporated by Reference 

(i) You must use PIAGGIO AERO 

INDUSTRIES S.p.A Service Bulletin 

(Mandatory) N.: 80–0278, dated July 15, 

2009; PIAGGIO P.180 AVANTI Maintenance 

Manual Temporary Revisions No. 33 and 34, 

both dated July 7, 2009; and PIAGGIO P.180 

AVANTI II Maintenance Manual Temporary 

Revisions No. 31 and 41, both dated July 7, 

2009, 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 Piaggio Aero Industries 

S.p.a., Via Cibrario, 4—16154 Genoa, Italy; 

fax: +39 010 6481 881; Internet: http:// 

www.piaggioaero.com. 

(3) You may review copies of the service 

information incorporated by reference for 

this AD at the FAA, Central Region, Office of 

the Regional Counsel, 901 Locust, Kansas 

City, Missouri 64106. For information on the 

availability of this material at the Central 

Region, call (816) 329–3768. 

(4) You may also review copies of the 

service information incorporated by reference 

for this AD 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 Kansas City, Missouri, on April 

19, 2010. 

John R. Colomy, 

Acting Manager, Small Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2010–9609 Filed 4–28–10; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2010–0381; Directorate 

Identifier 2009–NM–146–AD; Amendment 

39–16268; AD 2010–09–03] 

RIN 2120–AA64 

Airworthiness Directives; The Boeing 

Company Model 747–200B Series 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule; request for 

comments. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for certain 

Model 747–200B series airplanes. This 

AD requires repetitive inspections for 

cracking of the fuselage skin lap joints 

at stringer 6 on the left and right sides 

from station (STA) 340 to STA 400, a 

one-time general visual inspection to 

determine if certain fasteners are 

installed and to determine if service 

repair manual (SRM) repairs or repair 

doublers are installed, and corrective 

actions if necessary. Doing an optional 

modification of the stringer 6 lap joints 

terminates the repetitive inspections for 

the modified area. This AD results from 

reviews done by Boeing, which show 

that airplanes that were modified by 

Boeing to the stretched upper deck 

(SUD) configuration require inspection 

for cracking of the stringer 6 lap joint 

upper-fastener row earlier than 

previously expected. We are issuing this 

AD to detect and correct cracking of the 

stringer 6 lap joints where certain 

external doublers were not installed, 

which could result in rapid 

decompression and loss of structural 

integrity of the airplane. 

DATES: This AD is effective May 14, 

2010. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in the AD 

as of May 14, 2010. 

We must receive comments on this 

AD by June 28, 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 

W12–140, 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 Boeing Commercial 

Airplanes, Attention: Data & Services 

Management, P.O. Box 3707, MC 2H–65, 

Seattle, Washington 98124–2207; 

telephone 206–544–5000, extension 1; 

fax 206–766–5680; e-mail 

me.boecom@boeing.com; Internet 

https://www.myboeingfleet.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– 

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Federal Register / Vol. 75, No. 82 / Thursday, April 29, 2010 / Rules and Regulations 22515 

5527) is in the ADDRESSES section. 

Comments will be available in the AD 

docket shortly after receipt. 

FOR FURTHER INFORMATION CONTACT: Ivan 

Li, Aerospace Engineer, Airframe 

Branch, ANM–120S, FAA, Seattle 

Aircraft Certification Office, 1601 Lind 

Avenue, SW., Renton, Washington 

98057–3356; telephone (425) 917–6437; 

fax (425) 917–6590. 

SUPPLEMENTARY INFORMATION: 

Discussion 

Review by Boeing has determined that 

airplanes that were modified by Boeing 

to the stretched upper deck (SUD) 

configuration require inspecting the 

stringer 6 lap joint upper fastener row 

for cracking at an earlier time than 

expected. Previously, no inspections of 

this area were recommended prior to 

accomplishment of Boeing Service 

Bulletin 747–53–2272, Zone 1 

modification, which involves installing 

external doublers. If the external 

doublers have not been installed on the 

stringer 6 lap joints, cracks could 

develop in the lap joints. Skin cracks 

could join together and result in rapid 

decompression and loss of structural 

integrity of the airplane. 

Relevant Service Information 

We reviewed Boeing Alert Service 

Bulletin 747–53A2809, dated June 18, 

2009. This service bulletin specifies 

that, for airplanes with external 

doublers installed in accordance with 

Boeing Service Bulletin 747–53–2272, 

no further work is necessary. 

For the other affected airplanes, 

Boeing Alert Service Bulletin 747– 

53A2809, dated June 18, 2009, describes 

procedures for repetitive external 

detailed and high frequency eddy 

current (HFEC) inspections to detect 

cracking of the left and right side 

stringer 6 lap joints, doing a one-time 

general visual inspection to determine 

whether certain fasteners exist in the 

upper-fastener row of the lap joints and 

to determine whether any service repair 

manual (SRM) repairs or repair doublers 

are installed, and corrective actions if 

necessary. Corrective actions include 

repairing any cracks that are found, and 

contacting Boeing for repair instructions 

if certain fasteners, or if any SRM 

repairs or repair doublers other than 

those installed per Boeing Service 

Bulletin 747–53–2272, 

Zone 1 modification, are found in the 

inspection area. 

Boeing Alert Service Bulletin 747– 

53A2809, dated June 18, 2009, also 

specifies that the optional 

accomplishment of a modification 

would eliminate the need to do the 

repetitive inspections, repair cracks, or 

contact Boeing for instructions if certain 

fasteners are found. This modification 

involves removing the upper row of 

fasteners at the stringer 6 lap joints from 

STA 340 to STA 400 doing open-hole 

HFEC inspections to detect skin cracks; 

and doing corrective actions if necessary 

(e.g., trimming out any cracks found 

during any inspection), and installing 

external doublers as specified in the 

Zone 1 modification of Boeing Service 

Bulletin 747–53–2272. 

The compliance time for the initial 

inspections is 10,000 flight cycles after 

the airplane was modified to the SUD 

configuration, or within 50 flight cycles 

after the date on Boeing Alert Service 

Bulletin 747–53A2809, whichever 

occurs later. The repetitive interval is 

3,000 flight cycles. The compliance time 

for the corrective actions is before 

further flight. 

FAA’s Determination and Requirements 

of This AD 

No Model 747–200B series airplanes 

affected by this AD are on the U.S. 

Register. We are issuing this AD because 

the unsafe condition described 

previously is likely to exist or develop 

on other products of the same type 

design that could be registered in the 

United States in the future. This AD 

requires repetitive inspections of the left 

and right side stringer 6 lap joints from 

STA 340 to STA 400. 

Since no U.S. Model 747–200B series 

airplanes are affected by this AD, notice 

and opportunity for public comment 

before issuing this AD are unnecessary. 

Differences Between the AD and the 

Service Information 

Boeing Alert Service Bulletin 747– 

53A2809, dated June 18, 2009, specifies 

to contact the manufacturer for 

instructions on how to repair certain 

conditions, but this AD would require 

repairing those conditions in one of the 

following ways: 

• Using a method that we approve; or 

• Using data that meet the 

certification basis of the airplane, and 

that have been approved by the Boeing 

Commercial Airplanes Organization 

Designation Authorization (ODA) that 

has been authorized by the Manager, 

Seattle ACO, to make those findings. 

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– 

2010–0381; Directorate Identifier 2009– 

NM–146–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 

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 this AD: 

(1) Is not a ‘‘significant regulatory 

action’’ under Executive Order 12866, 

(2) Is not a ‘‘significant rule’’ under 

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. 

You can find our regulatory 

evaluation and the estimated costs of 

compliance in the AD docket. 

mstockstill on DSKH9S0YB1PROD with RULES

22516 Federal Register / Vol. 75, No. 82 / Thursday, April 29, 2010 / Rules and Regulations 

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: 

2010–09–03 The Boeing Company: 

Amendment 39–16268. Docket No. 

FAA–2010–0381; Directorate Identifier 

2009–NM–146–AD. 

Effective Date 

(a) This airworthiness directive (AD) is 

effective May 14, 2010. 

Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to The Boeing 

Company Model 747–200B series airplanes, 

certificated in any category, identified as 

Group 1, Configuration 2, in Boeing Alert 

Service Bulletin 747–53A2809, dated June 

18, 2009. 

Subject 

(d) Air Transport Association (ATA) of 

America Code 53: Fuselage. 

Unsafe Condition 

(e) This AD results from reviews done by 

Boeing, which show that airplanes modified 

to the stretched upper deck (SUD) 

configuration by Boeing require inspection 

for cracking of the upper-fastener row of the 

left and right side stringer 6 lap joints earlier 

than expected. The Federal Aviation 

Administration is issuing this AD to detect 

and correct cracking of the stringer 6 lap 

joints where certain external doublers were 

not installed, which could result in rapid 

decompression and loss of 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. 

Inspections 

(g) Except as required by paragraphs (h) 

and (i) of this AD: At the applicable time 

specified in paragraph 1.E., ‘‘Compliance,’’ of 

Boeing Alert Service Bulletin 747–53A2809, 

dated June 18, 2009, do the inspections 

specified in paragraphs (g)(1) and (g)(2) of 

this AD, and applicable corrective actions, in 

accordance with the Accomplishment 

Instructions of Boeing Alert Service Bulletin 

747–53A2809, dated June 18, 2009. Do all 

applicable corrective actions before further 

flight. Repeat the inspections specified in 

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

intervals not to exceed 3,000 flight cycles, 

except as provided by paragraph (j) of this 

AD. 

(1) Inspect the left and right side stringer 

6 lap joints from station (STA) 340 to STA 

400. The inspections include external 

detailed and high frequency eddy current 

(HFEC) inspections for cracks in the skin in 

areas that have not been modified or repaired 

as specified in paragraph 3.B., Part 2 or Part 

3, respectively, of the Accomplishment 

Instructions of Boeing Alert Service Bulletin 

747–53A2809, dated June 18, 2009. 

(2) Do a one-time general visual inspection 

of the lap joints to determine if certain 

fasteners are installed and to determine if 

structural repair manual (SRM) repairs or 

repair doublers are installed. 

Note 1: For airplanes on which external 

doublers have been installed on both side of 

the airplanes in accordance with Boeing 

Service Bulletin 747–53–2272, Zone 1 

modification, no further work is necessary. 

Exceptions to Service Bulletin 

(h) Where Boeing Alert Service Bulletin 

747–53A2809, dated June 18, 2009, specifies 

a compliance time after the date on that 

service bulletin, this AD requires compliance 

within the specified compliance time after 

the effective date of this AD. 

(i) For any condition in which Boeing Alert 

Service Bulletin 747–53A2809, dated June 

18, 2009, specifies to contact Boeing for 

appropriate action: those actions must be 

approved using a method approved in 

accordance with the procedures specified in 

paragraph (k) of this AD. 

Optional Terminating Action 

(j) Accomplishing the modification, 

including the open-hole HFEC inspections to 

detect skin cracks, and applicable corrective 

actions, specified in paragraph 3.B., Part 2, of 

the Accomplishment Instructions of Boeing 

Alert Service Bulletin 747–53A2809, dated 

June 18, 2009, terminates the repetitive 

inspections and repair requirements 

specified in paragraph (g) of this AD for the 

side of the airplane on which the 

modification is done. 

Alternative Methods of Compliance 

(AMOCs) 

(k)(1) The Manager, Seattle Aircraft 

Certification Office (ACO), 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: Ivan 

Li, Aerospace Engineer, Airframe Branch, 

ANM–120S, FAA, Seattle ACO, 1601 Lind 

Avenue, SW., Renton, Washington 98057– 

3356; telephone (425) 917–6437; fax (425) 

917–6590. Or, e-mail information to 9–ANM– 

Seattle-ACO–AMOC–Requests@faa.gov. 

(2) To request a different method of 

compliance or a different compliance time 

for this AD, follow the procedures in 14 CFR 

39.19. 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. 

(3) An AMOC that provides an acceptable 

level of safety may be used for any repair 

required by this AD if it is approved by the 

Boeing Commercial Airplanes Organization 

Designation Authorization (ODA) that has 

been authorized by the Manager, Seattle ACO 

to make those findings. For a repair method 

to be approved, the repair must meet the 

certification basis of the airplane, and the 

approval must specifically refer to this AD. 

Material Incorporated by Reference 

(l) You must use Boeing Alert Service 

Bulletin 747–53A2809, dated June 18, 2009, 

to do the actions required by this AD, unless 

the AD specifies otherwise. If you 

accomplish the optional terminating actions 

specified by this AD, you must use Boeing 

Alert Service Bulletin 747–53A2809, dated 

June 18, 2009, as applicable, to perform those 

actions, 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 Boeing Commercial 

Airplanes, Attention: Data & Services 

Management, P.O. Box 3707, MC 2H–65, 

Seattle, Washington 98124–2207; telephone 

206–544–5000, extension 1; fax 206–766– 

5680; e-mail me.boecom@boeing.com; 

Internet https://www.myboeingfleet.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. 

(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 April 9, 

2010. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service.. 

[FR Doc. 2010–9091 Filed 4–28–10; 8:45 am] 

BILLING CODE 4910–13–P 

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