Federal Register / Vol. 75, No. 198 / Thursday, October 14, 2010 / Rules and Regulations 63045 

TABLE 2—FOKKER CREDIT SERVICE BULLETINS

Fokker Service Bulletins Revision Date 

Fokker Performa Service Bulletin SBF100–32–127, including Appendix XIV, dated February 1, 

2006.

Original ......................... July 20, 2001. 

Fokker Performa Service Bulletin SBF100–32–127, including Appendix XIV, dated February 1, 

2006.

1 .................................... March 6, 2009. 

Fokker Service Bulletin SBF100–32–156 ........................................................................................... Original ......................... March 6, 2009. 

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, 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: 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 

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 2009–0176, 

dated August 6, 2009; and Fokker Service 

Bulletin SBF100–32–156, Revision 1, dated 

June 29, 2009; for related information. 

Material Incorporated by Reference 

(j) You must use Fokker Service Bulletin 

SBF100–32–156, Revision 1, dated June 29, 

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 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.myfokkerfleetcom. 

(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 

September 29, 2010. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2010–25449 Filed 10–13–10; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2010–0642; Directorate 

Identifier 2007–NM–332–AD; Amendment 

39–16470; AD 2010–21–10] 

RIN 2120–AA64 

Airworthiness Directives; BAE 

SYSTEMS (OPERATIONS) LIMITED 

Model BAe 146 and Avro 146–RJ 

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: 

* * * [F]uel leaks and failed fasteners 

[have been reported] in the region of the rear 

spar root joint attachment fitting at wing rib 

2. * * * 

* * * * * 

The unsafe condition is stress corrosion 

failures in the region of the rear spar 

root joint attachment fitting at wing rib 

2, which could lead to reduced 

structural integrity of the wing, and 

consequent reduced controllability of 

the airplane. We are issuing this AD to 

require actions to correct the unsafe 

condition on these products. 

DATES: This AD becomes effective 

November 18, 2010. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of November 18, 2010. 

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: 

Todd Thompson, Aerospace Engineer, 

International Branch, ANM–116, 

Transport Airplane Directorate, FAA, 

1601 Lind Avenue, SW., Renton, 

Washington 98057–3356; telephone 

(425) 227–1175; 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 July 1, 2010 (75 FR 38058). 

That NPRM proposed to correct an 

unsafe condition for the specified 

products. The MCAI states: 

British Aerospace originally issued Service 

Bulletin (SB) 57–033 in 1989 to detect fuel 

leaks and failed fasteners in the region of the 

rear spar root joint attachment fitting at wing 

rib 2. Accomplishment of this SB was 

mandated by the [Civil Aviation Authority] 

CAA United Kingdom AD 044–09–89. 

Revisions 1 through 7 of this SB were 

introduced to inspect pre mod HCM01447A 

standard installations for fuel leaks and loose 

or broken bolts. Modification HCM01447A 


emcdonald on DSK2BSOYB1PROD with RULES
63046 Federal Register / Vol. 75, No. 198 / Thursday, October 14, 2010 / Rules and Regulations 

introduced tension bolts in the attachment 

fitting instead of the previous Hi-Lok bolts. 

Revision 8 of the SB introduced inspection 

instructions for post modification 

HCM01447A installations because fuel tank 

leaks and failed fasteners have subsequently 

been found on aircraft post modification 

HCM01447A. Inspections of the post-mod 

HCM01447A standard are required to 

maintain the structural integrity of the wing. 

BAE Systems has now published SB 57–033 

Revision 9 that specifies additional, calendartime based, inspection criteria to control the 

stress corrosion failures of the pre and post 

modification HCM01447A installations. 

EASA AD 2007–0270 supersedes CAA UK 

AD 044–09–89 and requires the 

accomplishment of inspections and 

corrective actions, as necessary, in 

accordance with BAE Systems SB 57–033 

Revision 9. 

This [EASA] AD [2007–0270 R1] is revised 

to clarify that the calendar compliance times 

are to be counted from the effective date, not 

from the SB issue date. 

The unsafe condition is stress corrosion 

failures in the region of the rear spar 

root joint attachment fitting at wing rib 

2, which could lead to reduced 

structural integrity of the wing, and 

consequent reduced controllability of 

the airplane. Required actions include a 

general inspection to identify the type of 

bolt and nut at each location, external 

inspections of the bolt installation of the 

fuel tanks, related investigative actions, 

and corrective actions, as applicable. 

The general inspection includes 

identifying the type of bolt and nut at 

each location. 

External inspections of the bolt 

installation include: 

• Visually inspecting for proper nut 

installation, nut seating, and fuel 

seepage. 

• Checking for gaps between the 

fitting and wing structure. 

• Checking the nuts with a suitable 

torque spanner to the specifications in 

the torque figures shown in Table 2. of 

the Accomplishment Instructions of 

BAE SYSTEMS (OPERATIONS) 

LIMITED Inspection Service Bulletin 

ISB.57–033, Revision 9, dated October 

10, 2006, if Hi-Loks are installed, and 

• Doing either an ultrasonic 

inspection for damaged bolts or torque 

check of the tension bolts. 

Related investigative actions include: 

• Inspecting the condition of the 

sealant at and around all rear spar root 

joint attachment bolts. 

• Checking the bolt for damage or 

evidence of the nut being tightened to 

the end of the thread. 

• Examining the wear pattern on the 

seating surfaces of the bolt and nut to 

determine if the bolt and nut have been 

evenly seated on the structure. 

• Visually inspecting the bolt hole 

and surrounding area for damage, and 

• Confirming that the hole edge 

radius on the forward face of the rear 

spar complies with the specifications in 

Table 4 of the Accomplishment 

Instructions of BAE SYSTEMS 

(OPERATIONS) LIMITED Inspection 

Service Bulletin ISB.57–033, Revision 9, 

dated October 10, 2006. 

Corrective actions include either 

replacing the bolt, or repairing the 

defect in accordance with approved 

repair data from BAE Systems. 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. 

Explanation of Change to Applicability 

We have revised the applicability of 

the existing AD to identify model 

designations as published in the most 

recent type certificate data sheet for the 

affected models. 

Conclusion 

We reviewed the available data, and 

determined that air safety and the 

public interest require adopting the AD 

with the changes described previously. 

We determined that these changes will 

not increase the economic burden on 

any operator or increase the scope of the 

AD. 

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 1 

product of U.S. registry. We also 

estimate that it will take about 3 workhours per product to comply with the 

basic requirements of this AD. The 

average labor rate is $85 per work-hour. 

Based on these figures, we estimate the 

cost of this AD to the U.S. operators to 

be $255. 

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:// 

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. 


emcdonald on DSK2BSOYB1PROD with RULES
Federal Register / Vol. 75, No. 198 / Thursday, October 14, 2010 / Rules and Regulations 63047 

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: 

2010–21–10 BAE SYSTEMS 

(OPERATIONS) LIMITED: Amendment 

39–16470. Docket No. FAA–2010–0642; 

Directorate Identifier 2007–NM–332–AD. 

Effective Date 

(a) This airworthiness directive (AD) 

becomes effective November 18, 2010. 

Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to all BAE Systems 

(OPERATIONS) LIMITED Model BAe 146– 

100A, –200A, and –300A airplanes, and 

Model Avro 146–RJ70A, 146–RJ85A, and 

146–RJ100A airplanes, certificated in any 

category. 

Subject 

(d) Air Transport Association (ATA) of 

America Code 57: Wings. 

Reason 

(e) The mandatory continuing 

airworthiness information (MCAI) states: 

* * * [F]uel leaks and failed fasteners 

[have been reported] in the region of the rear 

spar root joint attachment fitting at wing rib 

2. * * * 

* * * * * 

The unsafe condition is stress corrosion 

failures in the region of the rear spar root 

joint attachment fitting at wing rib 2, which 

could lead to reduced structural integrity of 

the wing, and consequent reduced 

controllability 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. 

Actions 

(g) At the applicable time in paragraph 

(g)(1) or (g)(2) of this AD, do a general visual 

inspection to identify the type of bolt and nut 

at each location, in accordance with the 

Accomplishment Instructions of BAE 

SYSTEMS (OPERATIONS) LIMITED 

Inspection Service Bulletin ISB.57–033, 

Revision 9, dated October 10, 2006. 

(1) For airplanes on which neither 

Modification HCM01447A nor repair 

information leaflet (RIL) HC536H9156 (at any 

location) has been done as of the effective 

date of this AD, the compliance time for the 

inspection is at the later of the times 

specified in paragraphs (g)(1)(i) and (g)(1)(ii) 

of this AD. 

(i) Within 12 months after the effective 

date of this AD, or within 2 years after the 

last inspection done in accordance with BAE 

SYSTEMS (OPERATIONS) LIMITED 

Inspection Service Bulletin ISB.57–033, 

whichever occurs later, without exceeding 

4,000 flight cycles after the last inspection. 

(ii) Within 250 flight cycles or 3 months 

after the effective date of this AD, whichever 

occurs first. 

(2) For airplanes on which either 

Modification HCM01447A or RIL 

HC536H9156 (at any location) has been done 

as of the effective date of this AD, the 

compliance time for the inspection is at the 

latest of the times specified in paragraphs 

(g)(2)(i), (g)(2)(ii), and (g)(2)(iii) of this AD. 

(i) Before the accumulation of 4,000 total 

flight cycles. 

(ii) Within 4,000 flight cycles after all bolts 

are inspected and replaced in accordance 

with BAE SYSTEMS (OPERATIONS) 

LIMITED Inspection Service Bulletin ISB.57– 

033. 

(iii) Within 12 months after the effective 

date of this AD. 

(h) At the applicable time in paragraph 

(g)(1) or (g)(2) of this AD, do detailed 

inspections of the bolt installation for proper 

nut installation, nut seating, and fuel 

seepage; a detailed inspection for gaps 

between the fitting and wing structure; if HiLoks are installed, measure the torque of the 

nuts to determine the specifications in the 

torque figures shown in Table 2. of the 

Accomplishment Instructions of BAE 

SYSTEMS (OPERATIONS) LIMITED 

Inspection Service Bulletin ISB.57–033, 

Revision 9, dated October 10, 2006; and 

either an ultrasonic inspection for damaged 

bolts or a torque measurement of the tension 

bolts to determine the specifications in the 

torque figures shown in Table 3 of the 

Accomplishment Instructions of BAE 

SYSTEMS (OPERATIONS) LIMITED 

Inspection Service Bulletin ISB.57–033, 

Revision 9, dated October 10, 2006. Do all 

actions in accordance with the 

Accomplishment Instructions of BAE 

SYSTEMS (OPERATIONS) LIMITED 

Inspection Service Bulletin ISB.57–033, 

Revision 9, dated October 10, 2006. 

(i) If, during any inspection required by 

paragraph (h) of this AD, any defect (e.g., 

evidence of fuel seepage, damaged bolts or 

low bolt torque, loose or rotating nuts, 

suspect integrity of the bolt/nut assembly, or 

gaps between the fitting and wing structure) 

is found, before further flight, do the actions 

specified in paragraphs (i)(1), (i)(2), (i)(3), 

(i)(4), and (i)(5) of this AD, in accordance 

with the Accomplishment Instructions of 

BAE SYSTEMS (OPERATIONS) LIMITED 

Inspection Service Bulletin ISB.57–033, 

Revision 9, dated October 10, 2006. 

(1) Do a detailed inspection of the sealant 

for cracks at and around all rear spar root 

joint attachment bolts. 

(2) Do a detailed inspection of the bolt for 

damage or evidence of the nut being 

tightened to the end of the thread. 

(3) Do a detailed inspection of the wear 

pattern on the seating surfaces of the bolt and 

nut to determine if the bolt and nut have 

been evenly seated on the structure. 

(4) Do a detailed inspection of the bolt hole 

and surrounding area for damage. 

(5) Do a detailed inspection to determine 

that the hole edge radius on the forward face 

of the rear spar meets the dimensions 

specified in Table 4 of the Accomplishment 

Instructions of BAE SYSTEMS 

(OPERATIONS) LIMITED Inspection Service 

Bulletin ISB.57–033, Revision 9, dated 

October 10, 2006. 

(j) If during any inspection required by 

paragraph (h) or (i) of this AD, any defects 

(e.g., evidence of fuel seepage, damaged bolts 

or low bolt torque, loose or rotating nuts, 

suspect integrity of the bolt/nut assembly, 

gaps between the fitting and wing structure, 

cracked sealant, bolt damage or evidence of 

the nut being tightened to the end of the 

thread, uneven seating of the bolt and nut, 

bolt hole and surrounding area damage, or 

hole edge radius out of dimensions specified 

in Table 4 of the Accomplishment 

Instructions of BAE SYSTEMS 

(OPERATIONS) LIMITED Inspection Service 

Bulletin ISB.57–033, Revision 9, dated 

October 10, 2006), is found, before further 

flight, do all applicable correction actions, 

which include either replacing the bolt or 

repairing the defect, in accordance with the 

Accomplishment Instructions of BAE 

SYSTEMS (OPERATIONS) LIMITED 

Inspection Service Bulletin ISB.57–033, 

Revision 9, dated October 10, 2006. 

(k) Repeat the inspections in paragraph (h) 

of this AD thereafter, at the applicable time 

specified in Table 1 of this AD, for each 

individual location. 

TABLE 1—COMPLIANCE TIMES FOR REPEAT INSPECTIONS

If the location has— Then repeat the inspection— 

A Hi-Lok bolt ............................................................................................. Within 4,000 flight cycles or 24 months, whichever occurs earlier, after 

doing the last inspection. 

A tension bolt that was not replaced during the inspections in paragraphs (h) and (i) of this AD and no defects were found.Within 8,000 flight cycles or 48 months, whichever occurs earlier, after 

doing the last inspection. 


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63048 Federal Register / Vol. 75, No. 198 / Thursday, October 14, 2010 / Rules and Regulations 

TABLE 1—COMPLIANCE TIMES FOR REPEAT INSPECTIONS—Continued 

If the location has— Then repeat the inspection— 

A tension bolt that was replaced as required by paragraph (j) of this AD Within 4,000 flight cycles or 24 months, whichever occurs earlier after 

doing the replacement. 

A tension bolt that was not replaced and any defects were repaired as 

required by paragraph (j) of this AD.

Within 4,000 flight cycles or 24 months, whichever occurs earlier after 

doing the repair specified in paragraph (j) of this AD. 

FAA AD Differences 

Note 1: This AD differs from the MCAI 

and/or service information as follows: 

Although BAE SYSTEMS (OPERATIONS) 

LIMITED Service Bulletin ISB.57–033, 

Revision 9, dated October 10, 2006, allows 

additional time to rectify the defect for the 

corrective action depending on the condition, 

this AD requires rectifying the defect before 

further flight. 

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: Todd Thompson, 

Aerospace Engineer, International Branch, 

ANM–116, Transport Airplane Directorate, 

FAA, 1601 Lind Avenue, SW., Renton, 

Washington 98057–3356; telephone (425) 

227–1175; 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 

(m) Refer to MCAI European Aviation 

Safety Agency Airworthiness Directive 2007– 

0270 R1, dated November 7, 2007; and BAE 

SYSTEMS (OPERATIONS) LIMITED 

Inspection Service Bulletin ISB.57–033, 

Revision 9, dated October 10, 2006; for 

related information. 

Material Incorporated by Reference 

(n) You must use BAE SYSTEMS 

(OPERATIONS) LIMITED Inspection Service 

Bulletin ISB.57–033, Revision 9, dated 

October 10, 2006; 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 BAE SYSTEMS 

(OPERATIONS) LIMITED, Customer 

Information Department, Prestwick 

International Airport, Ayrshire, KA9 2RW, 

Scotland, United Kingdom; telephone +44 

1292 675207; fax +44 1292 675704; e-mail 

RApublications@baesystems.com; Internet 

http://www.baesystems.com/Businesses/ 

RegionalAircraft/index.htm. 

(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 

September 29, 2010. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2010–25469 Filed 10–13–10; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2010–0754 Directorate 

Identifier 2010–CE–039–AD; Amendment 

39–16475; AD 2010–21–15] 

RIN 2120–AA64 

Airworthiness Directives; Empresa 

Brasileira de Aeronautica S.A. 

(EMBRAER) Model EMB–500 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) 

issued 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: 

It has been found that certain regions of the 

elevators, elevators trim tabs, and ailerons do 

not present drain holes to avoid water 

accumulation inside of these flight control 

surfaces. Internal water accumulation may 

lead to flight control surfaces unbalancing 

possibly reducing the flutter margins, which 

could result in loss of airplane control. 

Since this condition may occur in other 

airplanes of the same type and affects flight 

safety, a corrective action is required. Thus, 

sufficient reason exists to request compliance 

with this AD in the indicated time limit. 

We are issuing this AD to require 

actions to correct the unsafe condition 

on these products. 

DATES: This AD becomes effective 

November 18, 2010. 

On November 18, 2010, the Director 

of the Federal Register approved the 

incorporation by reference of certain 

publications listed in this AD. 

ADDRESSES: You may examine the AD 

docket on the Internet at http:// 

www.regulations.gov or in person at 

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: Karl 

Schletzbaum, Aerospace Engineer, FAA, 

Small Airplane Directorate, 901 Locust, 

Room 301, Kansas City, Missouri 64106; 

telephone: (816) 329–4146; fax: (816) 

329–4090. 

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 August 3, 2010 (75 FR 

45558). That NPRM proposed to correct 

an unsafe condition for the specified 

products. The MCAI states: 

It has been found that certain regions of the 

elevators, elevators trim tabs, and ailerons do 


emcdonald on DSK2BSOYB1PROD with RULES