Federal Register / Vol. 75, No. 109 / Tuesday, June 8, 2010 / Rules and Regulations 32263 

Effective Date 

(a) This airworthiness directive (AD) 

becomes effective July 13, 2010. 

Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to CFM International, 

S.A. models CFM56–3 and –3B turbofan 

engines with 25 degrees midspan shroud fan 

blades, part numbers (P/Ns) 9527M99P08, 

9527M99P09, 9527M99P10, 9527M99P11, 

1285M39P01, or fan blade pairs, P/Ns 335– 

088–901–0, 335–088–902–0, 335–088–903–0, 

and 335–088–904–0 installed. These engines 

are installed on, but not limited to, Boeing 

737 series airplanes. 

(d) CFM International, S.A. has added to 

the basic engine model number on the engine 

nameplate to identify minor variations in 

engine configuration, installation 

components, or reduced ratings peculiar to 

aircraft installation requirements. 

(e) Those engines marked on the engine 

data plate as CFM56–3–B1 are included in 

this AD as CFM56–3 turbofan engines. 

(f) Those engines marked on the engine 

data plate as CFM56–3B–2 are included in 

this AD as CFM56–3B turbofan engines. 

Unsafe Condition 

(g) This AD results from a report of a failed 

fan blade with severe out-of-limit wear on the 

underside of the blade platform where it 

contacts the damper. We are issuing this AD 

to prevent failure of multiple fan blades, 

which could result in an uncontained failure 

of the engine and damage to the airplane. 

Compliance 

(h) You are responsible for having the 

actions required by this AD performed within 

the compliance times specified, unless the 

actions have already been done. 

Inspection for Wear 

(i) Within 900 cycles-in-service after the 

effective date of this AD, perform an on-wing 

or in-shop inspection of the fan blade and 

damper for wear. Use paragraphs 3.A.(1) 

through 3.A.(5) or paragraphs 3.B.(1) through 

3.B.(5) respectively, of the Accomplishment 

Instructions of CFM International Service 

Bulletin (SB) No. CFM56–3/3B/3C S/B 72– 

1067, dated February 15, 2007. 

(j) If you find out-of-limit wear on at least 

one fan blade platform underside, perform 

the additional inspections and disposition 

the parts, as specified in paragraphs 3.A.(3) 

and 3.A.(5) or paragraphs 3.B.(3) and 3.B.(5) 

respectively, of the Accomplishment 

Instructions of CFM International SB No. 

CFM56–3/3B/3C S/B 72–1067, dated 

February 15, 2007. 

(k) Thereafter, within intervals not to 

exceed 3,000 cycles-since-last inspection, 

perform an on-wing or in-shop inspection for 

wear. Use paragraphs 3.A.(1) through 3.A.(5) 

or paragraphs 3.B.(1) through 3.B.(5) 

respectively, of the Accomplishment 

Instructions of CFM International SB No. 

CFM56–3/3B/3C S/B 72–1067, dated 

February 15, 2007. 

(l) If you find wear on at least one fan blade 

platform underside, perform additional 

inspections and disposition the parts, as 

specified in paragraphs 3.A.(3) and 3.A.(5) or 

paragraphs 3.B.(3) and 3.B.(5) respectively, of 

the Accomplishment Instructions of CFM 

International SB No. CFM56–3/3B/3C S/B 

72–1067, dated February 15, 2007. 

Installation Prohibition 

(m) After the effective date of this AD, 

don’t install any 25 degrees midspan shroud 

fan blades, P/Ns 9527M99P08, 9527M99P09, 

9527M99P10, 9527M99P11, 1285M39P01, or 

fan blade pairs, P/Ns 335–088–901–0, 335– 

088–902–0, 335–088–903–0, and 335–088– 

904–0, unless they have passed an inspection 

specified in paragraph 3. of the 

Accomplishment Instructions of CFM 

International SB No. CFM56–3/3B/3C S/B 

72–1067, dated February 15, 2007. 

Optional Terminating Action 

(n) Replacing the 25 degrees midspan 

shroud fan blade set with a 37 degrees 

midspan shroud fan blade set terminates the 

repetitive inspection requirements specified 

in paragraph (k) of this AD. 

Alternative Methods of Compliance 

(o) The Manager, Engine Certification 

Office, has the authority to approve 

alternative methods of compliance for this 

AD if requested using the procedures found 

in 14 CFR 39.19. 

Related Information 

(p) Contact Antonio Cancelliere, Aerospace 

Engineer, Engine Certification Office, FAA, 

Engine & Propeller Directorate, 12 New 

England Executive Park, Burlington, MA 

01803; e-mail: antonio.cancelliere@faa.gov; 

telephone (781) 238–7751; fax (781) 238– 

7199, for more information about this AD. 

(q) European Aviation Safety Agency AD 

2009–0036, dated February 20, 2009, also 

addresses the subject of this AD. 

Material Incorporated by Reference 

(r) You must use CFM International Service 

Bulletin No. CFM56–3/3B/3C S/B 72–1067, 

dated February 15, 2007, to perform the 

inspections and parts dispositions required 

by this AD. The Director of the Federal 

Register approved the incorporation by 

reference of this service bulletin in 

accordance with 5 U.S.C. 552(a) and 1 CFR 

part 51. Contact CFM International, S. A., 

Technical Publication Department, 1 

Neumann Way, Cincinnati, OH 45215; 

telephone (513) 552–2800; fax (513) 552– 

2816, for a copy of this service information. 

You may review copies at the FAA, New 

England Region, 12 New England Executive 

Park, Burlington, MA; or 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/federalregister/cfr/ibr-locations.html. 

Issued in Burlington, Massachusetts, on 

May 25, 2010. 

Peter A. White, 

Assistant Manager, Engine and Propeller 

Directorate, Aircraft Certification Service. 

[FR Doc. 2010–13432 Filed 6–7–10; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2009–1223; Directorate 

Identifier 2009–NM–114–AD; Amendment 

39–16327; AD 2010–12–06] 

RIN 2120–AA64 

Airworthiness Directives; Bombardier, 

Inc. Model DHC–8–400 Series 

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: 

During final Acceptance Test Procedure 

(ATP), a small oil leak was discovered on the 

Spoiler Unload Valve and Rudder Shutoff 

Valve bodies. Investigation revealed that a 

number of valves were manufactured with an 

incorrect wall thickness. This thin wall 

condition caused cracking, subsequent 

external weeping and pressure loss from the 

subject valves. 

This condition, if not corrected, will cause 

a loss of hydraulic fluid and subsequent loss 

of spoiler and/or rudder control. 

* * * * * 

We are issuing this AD to require 

actions to correct the unsafe condition 

on these products. 

DATES: This AD becomes effective July 

13, 2010. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in this AD 

as of July 13, 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: 

Cesar Gomez, Aerospace Engineer, 

Airframe and Mechanical Systems 

Branch, ANE–171, FAA, New York 

Aircraft Certification Office, 1600 

Stewart Avenue, Suite 410, Westbury, 

New York 11590; telephone (516) 228– 

7318; fax (516) 794–5531. 

SUPPLEMENTARY INFORMATION: 


srobinson on DSKHWCL6B1PROD with RULES
32264 Federal Register / Vol. 75, No. 109 / Tuesday, June 8, 2010 / Rules and Regulations 

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 December 30, 2009 (74 FR 

69038). That NPRM proposed to correct 

an unsafe condition for the specified 

products. The MCAI states: 

During final Acceptance Test Procedure 

(ATP), a small oil leak was discovered on the 

Spoiler Unload Valve and Rudder Shutoff 

Valve bodies. Investigation revealed that a 

number of valves were manufactured with an 

incorrect wall thickness. This thin wall 

condition caused cracking, subsequent 

external weeping and pressure loss from the 

subject valves. 

This condition, if not corrected, will cause 

a loss of hydraulic fluid and subsequent loss 

of spoiler and/or rudder control. 

Revision 1 of this directive mandates a new 

interval for the initial inspection, clarifies the 

time for replacement of the valve(s) specified 

in Paragraphs 1.2 and 2.2, and clarifies the 

labeling of the inspected valves in Paragraph 

3 of this directive. 

Required actions include doing detailed 

inspections of the left-hand and righthand spoiler unload and rudder shutoff 

valve for leaking and weeping, replacing 

discrepant left-hand and right-hand 

spoiler unload and rudder shutoff 

valves with new or serviceable valves, 

and eventually replacing all valves 

having a certain part number. 

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 

considered the comment received. 

Request To Address Valves Inspected 

Previously 

Horizon Air requests that we address 

valves that have been inspected 

previously by the manufacturer by 

revising paragraphs (g)(1) and (g)(2) of 

the NPRM to include the phrase 

‘‘without suffix ‘A’ after the serial 

number.’’ Horizon Air explains that the 

NPRM, as written, requires the 

inspection to be done on all valves, 

regardless if they have been modified or 

unmodified. Horizon Air suggests that 

with the recommended phrasing, the 

NPRM would continue to require 

inspection of valves with the identified 

unsafe condition, but would not require 

inspection of valves inspected 

previously. 

We agree. Adding the phrase ‘‘without 

suffix ‘A’ after the serial number’’ will 

eliminate unnecessary inspections for 

valves that have been inspected 

previously by the manufacturer. We 

have revised paragraphs (g)(1) and (g)(2) 

of this AD accordingly. 

Conclusion 

We reviewed the available data, 

including the comment received, 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. 

Explanation of Change to Costs of 

Compliance 

Since issuance of the NPRM, we have 

increased the labor rate used in the 

Costs of Compliance from $80 per workhour to $85 per work-hour. The Costs of 

Compliance information, below, reflects 

this increase in the specified hourly 

labor rate. 

Costs of Compliance 

We estimate that this AD will affect 

61 products 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. 

Required parts will cost about $0 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 $15,555, or 

$255 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:// 

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, 


srobinson on DSKHWCL6B1PROD with RULES
Federal Register / Vol. 75, No. 109 / Tuesday, June 8, 2010 / Rules and Regulations 32265 

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: 

2010–12–06 Bombardier, Inc.: Amendment 

39–16327. Docket No. FAA–2009–1223; 

Directorate Identifier 2009–NM–114–AD. 

Effective Date 

(a) This airworthiness directive (AD) 

becomes effective July 13, 2010. 

Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to Bombardier, Inc. 

Model DHC–8–400, DHC–8–401, and DHC– 

8–402 series airplanes, certificated in any 

category, serial numbers 4105 through 4179 

inclusive. 

Subject 

(d) Air Transport Association (ATA) of 

America Code 27: Flight controls. 

Reason 

(e) The mandatory continuing 

airworthiness information (MCAI) states: 

During final Acceptance Test Procedure 

(ATP), a small oil leak was discovered on the 

Spoiler Unload Valve and Rudder Shutoff 

Valve bodies. Investigation revealed that a 

number of valves were manufactured with an 

incorrect wall thickness. This thin wall 

condition caused cracking, subsequent 

external weeping and pressure loss from the 

subject valves. 

This condition, if not corrected, will cause 

a loss of hydraulic fluid and subsequent loss 

of spoiler and/or rudder control. 

Revision 1 of this directive mandates a new 

interval for the initial inspection, clarifies the 

time for replacement of the valve(s) specified 

in Paragraphs 1.2 and 2.2, and clarifies the 

labeling of the inspected valves in Paragraph 

3 of this directive. 

Required actions include doing detailed 

inspections of the left-hand and right-hand 

spoiler unload and rudder shutoff valve for 

leaking and weeping, replacing discrepant 

left-hand and right-hand spoiler unload and 

rudder shutoff valves with new or serviceable 

valves, and eventually replacing all valves 

having a certain part number. 

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) Do the actions specified in paragraphs 

(g)(1), (g)(2), and (g)(3) of this AD, as 

applicable. 

(1) For airplanes having serial numbers 

4105 through 4172 inclusive: Within 750 

flight hours after the effective date of this AD, 

do a detailed inspection of the left-hand and 

right-hand spoiler unload valves having part 

number (P/N) 396000–1005 without suffix 

‘‘A’’ after the serial number, for leaking and 

weeping, in accordance with the 

Accomplishment Instructions of Bombardier 

Service Bulletin 84–27–37, dated February 5, 

2009. For airplanes with left-hand and righthand spoiler unload valves having P/N 

396000–1005 with suffix ‘‘A’’ after the serial 

number, no further action is required by this 

paragraph. 

(i) If any leaking or weeping is found, prior 

to further flight, replace the affected spoiler 

unload valve with a new or serviceable valve, 

in accordance with the Accomplishment 

Instructions of Bombardier Service Bulletin 

84–27–37, dated February 5, 2009. 

(ii) If no leaking and no weeping are found, 

replace the valves with new or serviceable 

valves within 6,000 flight hours after the 

initial inspection required by paragraph (g)(1) 

of this AD, in accordance with the 

Accomplishment Instructions of Bombardier 

Service Bulletin 84–27–37, dated February 5, 

2009. 

(2) For airplanes having serial numbers 

4113 through 4179 inclusive: Within 750 

flight hours after the effective date of this AD, 

do a detailed inspection of the left-hand and 

right-hand rudder shutoff valves having P/N 

412700–1001 without suffix ‘‘A’’ after the 

serial number, for leaking and weeping, in 

accordance with the Accomplishment 

Instructions of Bombardier Service Bulletin 

84–27–39, dated February 5, 2009. For 

airplanes with left-hand and right-hand 

rudder shutoff valves having P/N 412700– 

1001 with suffix ‘‘A’’ after the serial number, 

no further action is required by this 

paragraph. 

(i) If any leaking or weeping is found, prior 

to further flight, replace the affected rudder 

shutoff valve with a new or serviceable valve, 

in accordance with the Accomplishment 

Instructions of Bombardier Service Bulletin 

84–27–39, dated February 5, 2009. 

(ii) If no leaking and no weeping are found, 

replace the valves with new or serviceable 

valves within 6,000 flight hours after the 

initial inspection required by paragraph (g)(2) 

of this AD, in accordance with the 

Accomplishment Instructions of Bombardier 

Service Bulletin 84–27–39, dated February 5, 

2009. 

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

person may install a spoiler unload valve 

assembly having P/N 396000–1005, having a 

serial number from 0289 through 0424 

inclusive, or rudder shutoff valve having P/ 

N 412700–1001, having a serial number from 

0239 through 0384 inclusive, on any 

airplane, unless the valve has been inspected 

by the manufacturer and labeled with a suffix 

‘‘A’’ after the serial number. 

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, New York Aircraft 

Certification Office (ACO), ANE–170, 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: 

Program Manager, Continuing Operational 

Safety, FAA, New York ACO, 1600 Stewart 

Avenue, Suite 410, Westbury, New York, 

11590; telephone 516–228–7300; fax 516– 

794–5531. 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 Canadian Airworthiness 

Directive CF–2009–25R1, dated July 23, 

2009; Bombardier Service Bulletin 84–27–37, 

dated February 5, 2009; and Bombardier 

Service Bulletin 84–27–39, dated February 5, 

2009; for related information. 

Material Incorporated by Reference 

(j) You must use Bombardier Service 

Bulletin 84–27–37, dated February 5, 2009; 

or Bombardier Service Bulletin 84–27–39, 

dated February 5, 2009; 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 Bombardier, Inc., 400 CoˆteVertu Road West, Dorval, Que ́bec H4S 1Y9, 

Canada; telephone 514–855–5000; fax 514– 

855–7401; e-mail 

thd.qseries@aero.bombardier.com; Internet 

http://www.bombardier.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. 


srobinson on DSKHWCL6B1PROD with RULES
32266 Federal Register / Vol. 75, No. 109 / Tuesday, June 8, 2010 / Rules and Regulations 

Issued in Renton, Washington, on May 25, 

2010. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2010–13425 Filed 6–7–10; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2010–0171; Directorate 

Identifier 2009–NM–185–AD; Amendment 

39–16329; AD 2010–12–08] 

RIN 2120–AA64 

Airworthiness Directives; Airbus Model 

A300 Series Airplanes; Airbus Model 

A300 B4–600, B4–600R, and F4–600R 

Series Airplanes, and Model C4–605R 

Variant F Airplanes (Collectively Called 

A300–600 Series Airplanes); and Model 

A310 Series 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: 

During a maintenance check performed by 

an A310 operator, the recommended 

modification of the lower attachment beam of 

rack 101VU by accomplishment of Airbus 

Service Bulletin (SB) A310–53–2076 was 

embodied on the aeroplane, leading the 

operator to find three cracks on the FR15A 

crossbeam above the NLG [nose landing gear] 

box at the splicing with rack 107VU fitting. 

This condition, if not detected and 

corrected, could degrade the structural 

integrity of the crossbeam on NLG FR15A 

Web attachment fitting of rack 107VU. Rack 

107VU contains major airworthiness system 

components whose functioning could be 

adversely affected by the loss of the 

attachment fitting. 

As the A300 and A300–600 aeroplanes 

share this design feature, they are also 

affected. 

* * * * * 

We are issuing this AD to require 

actions to correct the unsafe condition 

on these products. 

DATES: This AD becomes effective July 

13, 2010. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in this AD 

as of July 13, 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: Dan 

Rodina, Aerospace Engineer, 

International Branch, ANM–116, 

Transport Airplane Directorate, FAA, 

1601 Lind Avenue, SW., Renton, 

Washington 98057–3356; telephone 

(425) 227–2125; fax (425) 227–1149. 

SUPPLEMENTARY INFORMATION: 

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 February 25, 2010 (75 FR 

8549). That NPRM proposed to correct 

an unsafe condition for the specified 

products. The MCAI states: 

During a maintenance check performed by 

an A310 operator, the recommended 

modification of the lower attachment beam of 

rack 101VU by accomplishment of Airbus 

Service Bulletin (SB) A310–53–2076 was 

embodied on the aeroplane, leading the 

operator to find three cracks on the FR15A 

crossbeam above the NLG [nose landing gear] 

box at the splicing with rack 107VU fitting. 

This condition, if not detected and 

corrected, could degrade the structural 

integrity of the crossbeam on NLG FR15A 

Web attachment fitting of rack 107VU. Rack 

107VU contains major airworthiness system 

components whose functioning could be 

adversely affected by the loss of the 

attachment fitting. 

As the A300 and A300–600 aeroplanes 

share this design feature, they are also 

affected. 

For the reasons stated above, this AD 

requires repetitive inspections for cracks of 

the crossbeam on NLG FR15A Web face 

attachment fitting of rack 107VU and 

corrective action, depending on findings. 

The corrective actions include 

contacting Airbus for repair 

instructions, and doing the repair if any 

crack is found. 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 

considered the comment received. The 

commenter, FedEx Express, supports 

the NPRM. 

Explanation of Change Made to This 

AD 

We have revised the subject header of 

this AD to identify the affected airplane 

models as published in the most recent 

type certificate data sheet. 

Conclusion 

We reviewed the available data, 

including the comment received, 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 

206 products of U.S. registry. We also 

estimate that it will take about 2 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 $35,020, or $170 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. 


srobinson on DSKHWCL6B1PROD with RULES