4480 Federal Register / Vol. 75, No. 18 / Thursday, January 28, 2010 / Rules and Regulations 

(2) Report the results of the inspection 

required by paragraph (f)(1) of this AD, 

including no findings, to Airbus, Customer 

Services Directorate, 1 Rond Point Maurice 

Bellonte, 31707 Blagnac Cedex France; Attn: 

SEDCC1 Technical Data and Documentation 

Services; Fax (+33) 5 61 93 28 06; e-mail 

sb.reporting@airbus.com; at the applicable 

time specified in paragraph (f)(2)(i) or 

(f)(2)(ii) of this AD. 

(i) If the inspection is done on or after the 

effective date of this AD: Submit the report 

within 30 days after the inspection. 

(ii) If the inspection was accomplished 

prior to 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 

(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: Vladimir 

Ulyanov, Aerospace Engineer, International 

Branch, ANM–116, Transport Airplane 

Directorate, FAA, 1601 Lind Avenue, SW., 

Renton, Washington 98057–3356; telephone 

(425) 227–1138; fax (425) 227–1149. Before 

using any approved AMOC on any airplane 

to which the AMOC applies, notify your 

principal maintenance inspector (PMI) or 

principal avionics inspector (PAI), as 

appropriate, or lacking a principal inspector, 

your local Flight Standards District Office. 

The AMOC approval letter must specifically 

reference this AD. 

(2) Airworthy Product: For any requirement 

in this AD to obtain corrective actions from 

a manufacturer or other source, use these 

actions if they are FAA-approved. Corrective 

actions are considered FAA-approved if they 

are approved by the State of Design Authority 

(or their delegated agent). You are required 

to assure the product is airworthy before it 

is returned to service. 

(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 European Aviation 

Safety Agency (EASA) Airworthiness 

Directive 2008–0223, dated December 15, 

2008, and the Airbus mandatory service 

bulletins listed in Table 1 of this AD, for 

related information. 

Material Incorporated by Reference 

(i) You must use the service information 

contained in Table 2 of this AD, as 

applicable, 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 Airbus SAS—Airworthiness 

Office—EAL, 1 Rond Point Maurice Bellonte, 

31707 Blagnac Cedex, France; fax +33 5 61 

93 45 80; e-mail airworthiness.A330- 

A340@airbus.com; Internet http:// 

www.airbus.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 or 425–227–1152. 

(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. 

TABLE 2—MATERIAL INCORPORATED

BY REFERENCE

Airbus Mandatory 

Service Bulletin— Dated— 

A330–32–3220 ............. October 10, 2008. 

A340–32–4264 ............. October 10, 2008. 

A340–32–5087 ............. October 10, 2008. 

Issued in Renton, Washington, on January 

14, 2010. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2010–1277 Filed 1–27–10; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2009–0912; Directorate 

Identifier 2009–NM–047–AD; Amendment 

39–16182; AD 2010–02–11] 

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: 

Reports have been received of finding 

corrosion at the Frame 29 wing-to-fuselage 

attachment lug plate joint. This condition, if 

not detected and corrected, could result in a 

degradation of the structural integrity of 

Frame 29 and the wing-to-fuselage 

attachment. 

* * * * * 

The unsafe condition is degradation of 

the structural integrity of Frame 29 and 

the wing-to-fuselage attachment, which 

could result in loss of control of the 

airplane. We are issuing this AD to 

require actions to correct the unsafe 

condition on these products. 

DATES: This AD becomes effective 

March 4, 2010. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of March 4, 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 October 19, 2009 (74 FR 

53433). That NPRM proposed to correct 

an unsafe condition for the specified 

products. The MCAI states: 

Reports have been received of finding 

corrosion at the Frame 29 wing-to-fuselage 

attachment lug plate joint. This condition, if 

not detected and corrected, could result in a 

degradation of the structural integrity of 

Frame 29 and the wing-to-fuselage 

attachment. 

The current method of inspecting the 

Frame 29 wing-to-fuselage attachment lug 

plate joint for corrosion is not considered 

adequate for finding corrosion in this 

particular area. 

To address this concern, BAE Systems 

(Operations) Limited has published 

Inspection Service Bulletin ISB.53–213, 

which replaces current Maintenance Review 

Board Report Structurally Significant Items 

Task 53–20–103 (equal to Maintenance 


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Federal Register / Vol. 75, No. 18 / Thursday, January 28, 2010 / Rules and Regulations 4481 

Planning Document Tasks 532003–DVI– 

10000–1, 532003–DVI–10000–2 and 532003– 

DVI–10000–3) and Corrosion Prevention and 

Control Programme Task C53–230–02–01. 

For the reason described above, this AD 

requires repetitive [detailed] inspections of 

the Frame 29 wing-to-fuselage attachment lug 

plate joint [for discrepancies, which are 

corrosion and fatigue cracking of the bolts 

and fastener bores; degraded, cracked, 

missing, and poor condition sealant] and 

repair(s) [which include replacing bolts, 

contacting BAE Systems for repair 

instructions and doing the repair, and reapplying sealant], as necessary. 

The unsafe condition is degradation of 

the structural integrity of Frame 29 and 

the wing-to-fuselage attachment, which 

could result in loss of control of the 

airplane. 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 Changes Made to This 

AD 

We have revised this AD to identify 

the legal name of the manufacturer as 

published in the most recent type 

certificate data sheet for the affected 

airplane models. 

Conclusion 

We reviewed the available data, and 

determined that air safety and the 

public interest require adopting the AD 

with the change described previously. 

We determined that this change 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 12 workhours per product to comply with the 

basic requirements of this AD. The 

average labor rate is $80 per work-hour. 

Based on these figures, we estimate the 

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

be $960. 

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. 

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: 

2010–02–11 BAE Systems (Operations) 

Limited: Amendment 39–16182. Docket 

No. FAA–2009–0912; Directorate 

Identifier 2009–NM–047–AD. 

Effective Date 

(a) This airworthiness directive (AD) 

becomes effective March 4, 2010. 

Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to BAE SYSTEMS 

(Operations) Limited Model BAe 146–100A, 

–200A, and –300A series airplanes; and BAE 

SYSTEMS (Operations) Limited Model Avro 

146–RJ70A, 146–RJ85A, and 146–RJ100A 

airplanes; certificated in any category; all 

serial numbers. 

Subject 

(d) Air Transport Association (ATA) of 

America Code 53: Fuselage. 

Reason 

(e) The mandatory continuing 

airworthiness information (MCAI) states: 

Reports have been received of finding 

corrosion at the Frame 29 wing-to-fuselage 

attachment lug plate joint. This condition, if 

not detected and corrected, could result in a 

degradation of the structural integrity of 

Frame 29 and the wing-to-fuselage 

attachment. 

The current method of inspecting the 

Frame 29 wing-to-fuselage attachment lug 

plate joint for corrosion is not considered 

adequate for finding corrosion in this 

particular area. 

To address this concern, BAE Systems 

(Operations) Limited has published 

Inspection Service Bulletin ISB.53–213, 

which replaces current Maintenance Review 

Board Report Structurally Significant Items 

Task 53–20–103 (equal to Maintenance 

Planning Document Tasks 532003–DVI– 

10000–1, 532003–DVI–10000–2 and 532003– 


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4482 Federal Register / Vol. 75, No. 18 / Thursday, January 28, 2010 / Rules and Regulations 

DVI–10000–3) and Corrosion Prevention and 

Control Programme Task C53–230–02–01. 

For the reason described above, this AD 

requires repetitive [detailed] inspections of 

the Frame 29 wing-to-fuselage attachment lug 

plate joint [for discrepancies, which are 

corrosion and fatigue cracking of the bolts 

and fastener bores; degraded, cracked, 

missing, and poor condition sealant] and 

repair(s) [which include replacing bolts, 

contacting BAE Systems for repair 

instructions and doing the repair and reapplying sealant], as necessary. 

The unsafe condition is degradation of the 

structural integrity of Frame 29 and the wingto-fuselage attachment, which could result in 

loss of control of the airplane. 

Actions and Compliance 

(f) Unless already done, do the following 

actions. 

(1) Within 24 months after the effective 

date of this AD, do a detailed inspection for 

discrepancies of the frame 29 wing-tofuselage attachment lug plate joint, in 

accordance with the Accomplishment 

Instructions of BAE SYSTEMS (Operations) 

Limited Inspection Service Bulletin ISB.53– 

213, dated May 21, 2008. 

Note 1: For the purposes of this AD, a 

detailed inspection is: ‘‘An intensive 

examination of a specific item, installation, 

or assembly to detect damage, failure, or 

irregularity. Available lighting is normally 

supplemented with a direct source of good 

lighting at an intensity deemed appropriate. 

Inspection aids such as mirror, magnifying 

lenses, etc., may be necessary. Surface 

cleaning and elaborate procedures may be 

required.’’ 

(2) Repeat the inspection required by 

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

intervals not to exceed 48 months. 

(3) During any inspection required by 

paragraph (f)(1) or (f)(2) of this AD, if it is not 

possible to replace a removed bolt with 

another bolt having the same part number as 

a replacement item, before further flight, 

contact BAE SYSTEMS to replace the 

removed bolt with an alternative bolt and do 

the approved BAE SYSTEMS repair. 

(4) If during any inspection required by 

paragraph (f)(1) or (f)(2) of this AD, any 

discrepancy is found, before further flight, 

repair in accordance with paragraph 2.C. of 

the Accomplishment Instructions of BAE 

SYSTEMS (Operations) Limited Inspection 

Service Bulletin ISB.53–213, dated May 21, 

2008. 

(5) Although BAE SYSTEMS (Operations) 

Limited Inspection Service Bulletin ISB.53– 

213, dated May 21, 2008, specifies to submit 

certain information to the manufacturer, this 

AD does not include that requirement. 

FAA AD Differences 

Note 2: This AD differs from the MCAI 

and/or service information as follows: 

Although BAE SYSTEMS (Operations) 

Limited Inspection Service Bulletin ISB.53– 

213, dated May 21, 2008; and European 

Aviation Safety Agency (EASA) AD 2009– 

0046, dated March 2, 2009; specify to submit 

certain information to the manufacturer, this 

AD does not include that requirement. 

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: 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. 

Related Information 

(h) Refer to MCAI EASA Airworthiness 

Directive 2009–0046, dated March 2, 2009; 

and BAE SYSTEMS (Operations) Limited 

Inspection Service Bulletin ISB.53–213, 

dated May 21, 2008; for related information. 

Material Incorporated by Reference 

(i) You must use BAE SYSTEMS 

(Operations) Limited Inspection Service 

Bulletin ISB.53–213, dated May 21, 2008, 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 Regional 

Aircraft, 13850 McLearen Road, Herndon, 

Virginia 20171; telephone 703–736–1080; email raebusiness@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 or 425–227–1152. 

(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 January 

14, 2010. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2010–1283 Filed 1–27–10; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2010–0047; Directorate 

Identifier 2009–SW–28–AD; Amendment 39– 

16177; AD 2010–02–07] 

RIN 2120–AA64 

Airworthiness Directives; Eurocopter 

France Model SE3160, SA315B, 

SA316B, SA316C, and SA319B 

Helicopters 

AGENCY: Federal Aviation 

Administration, DOT. 

ACTION: Final rule; request for 

comments. 

SUMMARY: This amendment supersedes 

an existing airworthiness directive (AD) 

for the specified Eurocopter France 

(Eurocopter) model helicopters. The 

existing AD requires certain inspections 

of a main rotor blade (blade) 

manufactured under a Parts 

Manufacturer Approval under 

Supplemental Type Certificate (STC) 

SH778GL. The AD requires inspecting 

each affected root end bolt (bolt) and 

bolt-hole for corrosion or a crack on the 

blade root end fitting (fitting) or in a 

bolt-hole. For certain serial-numbered 

blades, the AD also requires a one-time 

pull test on each fitting and blade root 

end doubler (doubler) to detect 

disbonding. This AD requires certain 

inspections for voids in any doubler or 

fitting and for paint cracks along the 

forward and aft edge of the blade fitting. 

Also, this AD requires inspecting the 

blade tip weight housing attachment. 

This AD also requires replacing 

unairworthy blades with airworthy 

blades. This amendment is prompted by 

reports from the STC holder of disbonds 

at the fittings, doublers, and the tip 

weight fitting. The actions specified by 

this AD are intended to prevent blade 

failure and subsequent loss of control of 

the helicopter. 

DATES: Effective February 12, 2010. 

The incorporation by reference of 

certain publications listed in the 

regulations is approved by the Director 

of the Federal Register as of February 

12, 2010. 


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