Federal Register / Vol. 74, No. 165 / Thursday, August 27, 2009 / Rules and Regulations 43625 

Adoption of the Amendment 

■ Accordingly, under the authority 

delegated to me by the Administrator, 

the Federal Aviation Administration 

amends part 39 of the Federal Aviation 

Regulations (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. FAA amends § 39.13 by adding the 

following new AD: 

2009–18–04 Air Tractor, Inc.: Amendment 

39–16000; Docket No. FAA–2009–0489; 

Directorate Identifier 2009–CE–025–AD. 

Effective Date 

(a) This AD becomes effective on October 

1, 2009. 

Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to Models AT–802 and 

AT–802A airplanes, serial numbers 802/ 

802A–001 through 802/802A–0319, that are 

certificated in any category. 

Unsafe Condition 

(d) This AD results from a report of the 

rudder pedal cable becoming jammed in 

flight. We are proposing this AD to prevent 

jamming of the rudder-aileron interconnect 

cables by unsecured items in the baggage 

compartment, which could result in failure of 

the rudder-aileron interconnect cable system. 

This failure could lead to loss of control. 

Compliance 

(e) To address this problem, you must do 

the following, unless already done: 

Actions Compliance Procedures 

(1) Secure any items stowed in the baggage 

compartment using tie down straps and/or a 

cargo net.

Before further flight after October 1, 2009 (the 

effective date of this AD) until the installation of the rudder-aileron interconnect cable 

shield kit required in paragraph (e)(2) of this 

AD is done.

Not applicable. 

(2) Install the following rudder-aileron interconnect cable shield kit, as applicable.No later than December 31, 2009 ................... Snow Engineering Co., Service Letter #274, 

Revision A, dated April 6, 2009. 

(i) For all airplanes equipped for agricultural spray operations and all fire-fighting 

airplanes retrofitted with Gen II Fire Retardant Delivery System relay box, install 

cable shield kit SL#274.

(ii) For all fire-fighting airplanes not 

equipped with Gen II Fire Retardant Delivery System relay box, install cable 

shield kit SL#274–2.

(iii) Installation of the applicable cable 

shield kit SL#274 or SL#274–2 terminates the requirement of paragraph 

(e)(1) of this AD.

Alternative Methods of Compliance 

(AMOCs) 

(f) The Manager, Fort Worth Airplane 

Certification 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: Andy McAnaul, 

Aerospace Engineer, 10100 Reunion Pl., Ste. 

650, San Antonio, Texas 78216; telephone: 

(210) 308–3365; fax: (210) 308–3370. 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. 

Material Incorporated by Reference 

(g) You must use Snow Engineering Co., 

Service Letter #274, Revision A, dated April 

6, 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 Air Tractor, Inc., P.O. Box 

485, Olney, Texas 76374; telephone: (940) 

564–5616; facsimile: (940) 564–5612; e-mail: 

parts@airtractor.com; Internet: http:// 

www.airtractor.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 August 

18, 2009. 

Scott A. Horn, 

Acting Manager, Small Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. E9–20385 Filed 8–26–09; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2009–0496; Directorate 

Identifier 2008–NM–139–AD; Amendment 

39–16001; AD 2009–18–05] 

RIN 2120–AA64 

Airworthiness Directives; Fokker 

Model F.27 Mark 050 and F.28 Mark 

0100 Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

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: 


srobinson on DSKHWCL6B1PROD with RULES
43626 Federal Register / Vol. 74, No. 165 / Thursday, August 27, 2009 / Rules and Regulations 

Several incidents have been reported 

where an electrical burning smell was noted 

in the cockpit, originating from the Electrical 

Power Centre. Troubleshooting revealed a 

partly molten terminal, which normally 

attaches a wire or bus bar to a stud of an 

Electrical Power Contactor, Part Number 

(P/N) SG02206. Furthermore, heat damage to 

the contactor stud itself was found. * * * 

* * * * * 

This condition, if not corrected, could lead 

to further cases of overheating of terminals 

and studs of Electrical Power Contactors 

P/N SG02206, possibly resulting in the loss 

of electrical power systems, electrical arcing 

and fire/smoke in the cockpit. 

* * * * * 

We are issuing this AD to require 

actions to correct the unsafe condition 

on these products. 

DATES: This AD becomes effective 

October 1, 2009. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in this AD 

as of October 1, 2009. 

ADDRESSES: You may examine the AD 

docket on the Internet at http:// 

www.regulations.gov or in person at the 

U.S. Department of Transportation, 

Docket Operations, M–30, West 

Building Ground Floor, Room W12–140, 

1200 New Jersey Avenue, SE., 

Washington, DC. 

FOR FURTHER INFORMATION CONTACT: Tom 

Rodriguez, Aerospace Engineer, 

International Branch, ANM–116, 

Transport Airplane Directorate, FAA, 

1601 Lind Avenue, SW., Renton, 

Washington 98057–3356; telephone 

(425) 227–1137; fax (425) 227–1149. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to include an AD that would 

apply to the specified products. That 

NPRM was published in the Federal 

Register on June 2, 2009 (74 FR 26322). 

That NPRM proposed to correct an 

unsafe condition for the specified 

products. The MCAI states: 

Several incidents have been reported 

where an electrical burning smell was noted 

in the cockpit, originating from the Electrical 

Power Centre. Troubleshooting revealed a 

partly molten terminal, which normally 

attaches a wire or bus bar to a stud of an 

Electrical Power Contactor, Part Number 

(P/N) SG02206. Furthermore, heat damage to 

the contactor stud itself was found. Material 

investigation revealed that the terminal, 

which was attached to the stud, was not 

properly torque tightened when the incident 

occurred. Loss of torque is considered to 

have occurred during operation, for reasons 

not fully understood. Further loosening may 

have taken place in-service under influence 

of vibration. As a result, poor contact caused 

electrical arcing during which extremely high 

temperatures were developed, leading to 

partial melting of the terminal. 

Investigation of some other burned 

contactors revealed evidence (flat spring lock 

washer) of a fully torqued terminal/stud 

connection when the overheating occurred. 

The exact cause for the increase in 

temperature in the contactor and the 

terminal/stud could not be determined. 

However, it could not be excluded that an 

increase of the temperature inside the 

contactor could lead to reduction of the 

reliability of the contactor stud/terminal 

connection due to loss of lock washer 

tension. The affected Electrical Power 

Contactor is used on several locations in the 

electrical power system, i.e., Generator Line 

Contactor (GLC), Bus Tie Contactor (BTC), 

Auxiliary Power Contactor (APC) and 

External Power Contactor (EPC). 

This condition, if not corrected, could lead 

to further cases of overheating of terminals 

and studs of Electrical Power Contactors 

P/N SG02206, possibly resulting in the loss 

of electrical power systems, electrical arcing 

and fire/smoke in the cockpit. 

For the reasons described above, this EASA 

Airworthiness Directive (AD) requires the 

replacement of the current nut and spring 

washer of the standard contactor P/N 

SG02206 with a new self-locking nut. 

You may obtain further information by 

examining the MCAI in the AD docket. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. We 

received no comments on the NPRM or 

on the determination of the cost to the 

public. 

Conclusion 

We reviewed the available data and 

determined that air safety and the 

public interest require adopting the AD 

as proposed. 

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 required different 

actions in this AD from those in the 

MCAI in order to follow our FAA 

policies. Any such differences are 

highlighted in a NOTE within the AD. 

Costs of Compliance 

We estimate that this AD will affect 5 

products of U.S. registry. We also 

estimate that it will take about 8 workhours per product to comply with the 

basic requirements of this AD. The 

average labor rate is $80 per work-hour. 

Required parts will cost about $5,715 

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 parts. 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 

this AD to the U.S. operators to be 

$31,775, or $6,355 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 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. 

Examining the AD Docket 

You may examine the AD docket on 

the Internet at http:// 


srobinson on DSKHWCL6B1PROD with RULES
Federal Register / Vol. 74, No. 165 / Thursday, August 27, 2009 / Rules and Regulations 43627 

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 the NPRM, 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. 

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: 

2009–18–05 Fokker Services B.V.: 

Amendment 39–16001. Docket No. 

FAA–2009–0496; Directorate Identifier 

2008–NM–139–AD. 

Effective Date 

(a) This airworthiness directive (AD) 

becomes effective October 1, 2009. 

Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to Fokker Model F.27 

Mark 050 and F.28 Mark 0100 airplanes, 

certificated in any category, all serial 

numbers. 

Subject 

(d) Air Transport Association (ATA) of 

America Code 24: Electrical power. 

Reason 

(e) The mandatory continuing 

airworthiness information (MCAI) states: 

Several incidents have been reported 

where an electrical burning smell was noted 

in the cockpit, originating from the Electrical 

Power Centre. Troubleshooting revealed a 

partly molten terminal, which normally 

attaches a wire or bus bar to a stud of an 

Electrical Power Contactor, Part Number 

(P/N) SG02206. Furthermore, heat damage to 

the contactor stud itself was found. Material 

investigation revealed that the terminal, 

which was attached to the stud, was not 

properly torque tightened when the incident 

occurred. Loss of torque is considered to 

have occurred during operation, for reasons 

not fully understood. Further loosening may 

have taken place in-service under influence 

of vibration. As a result, poor contact caused 

electrical arcing during which extremely high 

temperatures were developed, leading to 

partial melting of the terminal. 

Investigation of some other burned 

contactors revealed evidence (flat spring lock 

washer) of a fully torqued terminal/stud 

connection when the overheating occurred. 

The exact cause for the increase in 

temperature in the contactor and the 

terminal/stud could not be determined. 

However, it could not be excluded that an 

increase of the temperature inside the 

contactor could lead to reduction of the 

reliability of the contactor stud/terminal 

connection due to loss of lock washer 

tension. The affected Electrical Power 

Contactor is used on several locations in the 

electrical power system, i.e. Generator Line 

Contactor (GLC), Bus Tie Contactor (BTC), 

Auxiliary Power Contactor (APC) and 

External Power Contactor (EPC). 

This condition, if not corrected, could lead 

to further cases of overheating of terminals 

and studs of Electrical Power Contactors 

P/N SG02206, possibly resulting in the loss 

of electrical power systems, electrical arcing 

and fire/smoke in the cockpit. 

For the reasons described above, this EASA 

Airworthiness Directive (AD) requires the 

replacement of the current nut and spring 

washer of the standard contactor P/N 

SG02206 with a new self-locking nut. 

Actions and Compliance 

(f) Unless already done, do the following 

actions: 

(1) Except as provided by paragraphs (f)(2) 

and (f)(3) of this AD: Within 36 months after 

the effective date of this AD, remove the 

standard nuts and lock washers from the 

contactors having P/N SG02206, install new 

self-locking nuts, and perform the applicable 

tests on the Alternating Current Bus Transfer 

system, in accordance with the 

Accomplishment Instructions of Fokker 

Service Bulletin SBF100–24–041 or SBF50– 

24–031, both dated January 29, 2008, as 

applicable. If any test fails, before further 

flight, repair using a method approved by 

either the Manager, International Branch, 

ANM–116, Transport Airplane Directorate, 

FAA; or European Aviation Safety Agency 

(EASA) (or its delegated agent). 

(2) Accomplishment of paragraph (f)(1) of 

this AD is not required for Model F.28 Mark 

0100 airplanes that have been modified in 

service in accordance with Fokker Service 

Bulletin SBF100–24–037, dated October 2, 

2003. Accomplishment of Fokker Service 

Bulletin SBF100–24–037, dated October 2, 

2003, within the compliance time specified 

in paragraph (f)(1) of this AD is considered 

an acceptable method of compliance with the 

requirements of paragraph (f)(1) of this AD. 

(3) Accomplishment of paragraph (f)(1) of 

this AD is not required for Model F.27 Mark 

050 airplanes that have been modified during 

production to incorporate Fokker 

Engineering Change Record (ECR) 51780, or 

for airplanes that have been modified in 

service in accordance with Fokker Service 

Bulletin SBF50–24–030, dated November 6, 

2003. Accomplishment of Fokker Service 

Bulletin SBF50–24–030, dated November 6, 

2003, within the compliance time specified 

in paragraph (f)(1) of this AD is considered 

an acceptable method of compliance with the 

requirements of paragraph (f)(1) of this AD. 

(4) As of 36 months after the effective date 

of this AD, no person may install a contactor 

having P/N SG02206 on any airplane unless 

it has been modified in accordance with 

Goodrich Power Systems Service Bulletin 

SG02206–24–01, dated March 4, 2008. 

FAA AD Differences 

Note 1: This AD differs from the MCAI 

and/or service information as follows: The 

MCAI does not include a corrective action for 

airplanes on which the test required by 

paragraph (f)(1) of this AD fails. This AD 

requires the corrective action specified in 

paragraph (f)(1) 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, 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: Tom Rodriguez, 

Aerospace Engineer, International Branch, 

ANM–116, Transport Airplane Directorate, 

FAA, 1601 Lind Avenue, SW., Renton, 

Washington 98057–3356; telephone (425) 

227–1137; 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 EASA Airworthiness 

Directive 2008–0091, dated May 13, 2008, 

and the service information listed in Tables 

1, 2, and 3 of this AD for related information. 


srobinson on DSKHWCL6B1PROD with RULES
43628 Federal Register / Vol. 74, No. 165 / Thursday, August 27, 2009 / Rules and Regulations 

TABLE 1—SERVICE INFORMATION

Service bulletin Date 

Fokker Service Bulletin SBF50–24–030, including the drawings identified in Table 2 of this AD ......................................... November 6, 2003. 

Fokker Service Bulletin SBF50–24–031 .................................................................................................................................. January 29, 2008. 

Fokker Service Bulletin SBF100–24–037, including Manual Change Notification—Maintenance Documentation MCNM 

F100–076, dated October 2, 2003, and including the drawings identified in Table 3 of this AD.

October 2, 2003. 

Fokker Service Bulletin SBF100–24–041 ................................................................................................................................ January 29, 2008. 

Goodrich Power Systems Service Bulletin SG02206–24–01 ................................................................................................. March 4, 2008. 

TABLE 2—DRAWINGS INCLUDED IN FOKKER SERVICE BULLETIN SBF50–24–030 

Fokker drawing— Sheet— Issue— Dated— 

W7980–236 ........................................................... 02 H ........................................................................... August 1, 2003. 

W7980–253 ........................................................... 40 BK ......................................................................... September 17, 2003. 

W7980–253 ........................................................... 41 BK ......................................................................... September 17, 2003. 

W7980–253 ........................................................... 42 BK ......................................................................... September 17, 2003. 

W7980–253 ........................................................... 43 BK ......................................................................... September 17, 2003. 

W7980–253 ........................................................... 44 BL ......................................................................... September 17, 2003. 

W7980–253 ........................................................... 45 BK ......................................................................... September 17, 2003. 

W7980–253 ........................................................... 46 BL ......................................................................... September 17, 2003. 

W7980–253 ........................................................... 47 BK ......................................................................... September 17, 2003. 

W7980–253 ........................................................... 48 BK ......................................................................... September 17, 2003. 

W7980–253 ........................................................... 49 BL ......................................................................... September 17, 2003. 

W7980–253 ........................................................... 50 BL ......................................................................... September 17, 2003. 

W7980–253 ........................................................... 51 BL ......................................................................... September 17, 2003. 

W7980–253 ........................................................... 52 BL ......................................................................... September 17, 2003. 

W7980–253 ........................................................... 53 BL ......................................................................... September 17, 2003. 

W7980–253 ........................................................... 54 BK ......................................................................... September 17, 2003. 

W7980–253 ........................................................... 55 BL ......................................................................... September 17, 2003. 

W7980–253 ........................................................... 56 BL ......................................................................... September 17, 2003. 

W7980–253 ........................................................... 57 BK ......................................................................... September 17, 2003. 

W7980–253 ........................................................... 58 BL ......................................................................... September 17, 2003. 

W7980–253 ........................................................... 59 BK ......................................................................... September 17, 2003. 

W7980–253 ........................................................... 60 BK ......................................................................... September 24, 2003. 

W7980–253 ........................................................... 61 BK ......................................................................... September 24, 2003. 

W7980–253 ........................................................... 62 BK ......................................................................... September 24, 2003. 

W7980–253 ........................................................... 63 BL ......................................................................... September 24, 2003. 

W7980–253 ........................................................... 64 BK ......................................................................... September 24, 2003. 

W7980–253 ........................................................... 65 BL ......................................................................... September 24, 2003. 

W7980–253 ........................................................... 66 BK ......................................................................... September 24, 2003. 

TABLE 3—DRAWINGS INCLUDED IN FOKKER SERVICE BULLETIN SBF100–24–037 

Fokker drawing— Sheet— Issue— Dated— 

W43255 ................................................................. 01 A ........................................................................... July 30, 2003. 

W43255 ................................................................. 02 Original ................................................................. July 30, 2003. 

W43255 ................................................................. 03 A ........................................................................... August 4, 2003. 

W43255 ................................................................. 04 A ........................................................................... July 30, 2003. 

W43255 ................................................................. 05 Original ................................................................. July 30, 2003. 

W43255 ................................................................. 06 A ........................................................................... July 30, 2003. 

W43255 ................................................................. 07 A ........................................................................... August 4, 2003. 

Material Incorporated by Reference 

(i) You must use the service information 

contained in Table 4 of this AD, as 

applicable, to do the actions required by this 

AD, unless the AD specifies otherwise. If you 

do the optional actions specified in this AD, 

you must use the service information 

specified in Tables 2, 3, and 5 of this AD, as 

applicable, 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 Fokker service information 

identified in this AD, contact Fokker Services 

B.V., Technical Services Dept., P.O. Box 231, 

2150 AE Nieuw-Vennep, the Netherlands; 

telephone + 31 (0)252–627–350; fax + 31 

(0)252–627–211; e-mail 

technicalservices.fokkerservices@stork.com; 

Internet http://www.myfokkerfleet.com. 

(3) For Goodrich service information 

identified in this AD, contact Goodrich 

Corporation, Power Systems, 1555 Corporate 

Woods Parkway, Uniontown, Ohio 44685– 

8799; telephone 330–487–2007; fax 330–487– 

1902; e-mail 

twinsburg.techpubs@goodrich.com; Internet 

http://www.goodrich.com/TechPubs. 

(4) 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. 

(5) 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. 


srobinson on DSKHWCL6B1PROD with RULES
Federal Register / Vol. 74, No. 165 / Thursday, August 27, 2009 / Rules and Regulations 43629 

TABLE 4—DOCUMENTS INCORPORATED BY REFERENCE FOR ACTIONS REQUIRED BY THIS AD 

Service bulletin Date 

Fokker Service Bulletin SBF50–24–031 .................................................................................................................................. January 29, 2008. 

Fokker Service Bulletin SBF100–24–041 ................................................................................................................................ January 29, 2008. 

Goodrich Power Systems Service Bulletin SG02206–24–01 ................................................................................................. March 4, 2008. 

TABLE 5—DOCUMENTS INCORPORATED BY REFERENCE FOR OPTIONAL ACTIONS SPECIFIED IN THIS AD 

Service bulletin Date 

Fokker Service Bulletin SBF50–24–030 including the drawings identified in Table 2 of this AD .......................................... November 6, 2003. 

Fokker Service Bulletin SBF100–24–037, including Manual Change Notification—Maintenance Documentation MCNM 

F100–076, dated October 2, 2003, and including the drawings identified in Table 3 of this AD.

October 2, 2003. 

Issued in Renton, Washington, on August 

17, 2009. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. E9–20576 Filed 8–26–09; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2009–0477; Directorate 

Identifier 2008–NM–191–AD; Amendment 

39–16003; AD 2009–18–07] 

RIN 2120–AA64 

Airworthiness Directives; Boeing 

Model 747–100, –100B, –100B SUD, 

–200B, and –300 Series Airplanes; and 

Model 747SP and 747SR Series 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: The FAA is superseding an 

existing airworthiness directive (AD), 

which applies to certain Boeing Model 

747 series airplanes. That AD currently 

requires repetitive inspections to detect 

cracks in various areas of the fuselage 

internal structure, and related 

investigative/corrective actions if 

necessary. This new AD requires 

additional repetitive inspections for 

cracking of certain fuselage structure, 

and related investigative/corrective 

actions if necessary. This AD results 

from fatigue tests and analysis by 

Boeing that identified areas of the 

fuselage where fatigue cracks can occur. 

We are issuing this AD to prevent the 

loss of the structural integrity of the 

fuselage, which could result in rapid 

depressurization of the airplane. 

DATES: This AD becomes effective 

October 1, 2009. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in the AD 

as of October 1, 2009. 

ADDRESSES: 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 address for the 

Docket Office (telephone 800–647–5527) 

is the Document Management Facility, 

U.S. Department of Transportation, 

Docket Operations, M–30, West 

Building Ground Floor, Room W12–140, 

1200 New Jersey Avenue, SE., 

Washington, DC 20590. 

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 

The FAA issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to include an AD that 

supersedes AD 2005–20–30, amendment 

39–14327 (70 FR 59252, October 12, 

2005). The existing AD applies to 

certain Boeing Model 747 series 

airplanes. That NPRM was published in 

the Federal Register on May 26, 2009 

(74 FR 24712). That NPRM proposed to 

continue to require repetitive 

inspections to detect cracks in various 

areas of the fuselage internal structure, 

and related investigative/corrective 

actions if necessary. That NPRM also 

proposed to require additional repetitive 

inspections for cracking of certain 

fuselage structure, and related 

investigative/corrective actions if 

necessary. 

Comments 

We provided the public the 

opportunity to participate in the 

development of this AD. We have 

considered the comment that has been 

received on the NPRM. Boeing concurs 

with the NPRM. 

Conclusion 

We have carefully reviewed the 

available data, including the comment 

that has been received, and determined 

that air safety and the public interest 

require adopting the AD as proposed. 

Costs of Compliance 

There are about 209 airplanes of the 

affected design in the worldwide fleet. 

The following table provides the 

estimated costs for U.S. operators to 

comply with this AD. The average labor 

rate is $80 per work hour. 


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