30274 Federal Register / Vol. 75, No. 104 / Tuesday, June 1, 2010 / Rules and Regulations 

Bulletin 863520–26–001, dated December 21, 

2009. 

(3) As of July 6, 2010 (the effective date of 

this AD), do not install any fire extinguisher 

listed in L’Hotellier Service Bulletin 863520– 

26–001, dated December 21, 2009, on any 

airplane, unless it has been overhauled with 

compliant Halon 1211 (BCF) and reidentified, in accordance with the 

instructions of L’Hotellier Service Bulletin 

863520–26–001, dated December 21, 2009. 

FAA AD Differences 

Note: This AD differs from the MCAI and/ 

or service information as follows: No 

differences. 

Other FAA AD Provisions 

(g) The following provisions also apply to 

this AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, Standards Office, 

FAA, has the authority to approve AMOCs 

for this AD, if requested using the procedures 

found in 14 CFR 39.19. Send information to 

ATTN: Albert Mercado, Aerospace Engineer, 

FAA, Small Airplane Directorate, 901 Locust, 

Room 301, Kansas City, Missouri 64106; 

telephone: (816) 329–4119; fax: (816) 329– 

4090. Before using any approved AMOC on 

any airplane to which the AMOC applies, 

notify your appropriate principal inspector 

(PI) in the FAA Flight Standards District 

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

FSDO. 

(2) Airworthy Product: For any 

requirement in this AD to obtain corrective 

actions from a manufacturer or other source, 

use these actions if they are FAA-approved. 

Corrective actions are considered FAAapproved if they are approved by the State 

of Design Authority (or their delegated 

agent). You are required to assure the product 

is airworthy before it is returned to service. 

(3) Reporting Requirements: For any 

reporting requirement in this AD, under the 

provisions of the Paperwork Reduction Act 

(44 U.S.C. 3501 et seq.), the Office of 

Management and Budget (OMB) has 

approved the information collection 

requirements and has assigned OMB Control 

Number 2120–0056. 

Related Information 

(h) Refer to MCAI EASA AD No.: 2010– 

0012, dated February 5, 2010; DAHER– 

SOCATA TBM Aircraft Mandatory Service 

Bulletin SB 70–183, dated January 2010; and 

L’Hotellier Service Bulletin 863520–26–001, 

dated December 21, 2009, for related 

information. 

Material Incorporated by Reference 

(i) You must use DAHER–SOCATA TBM 

Aircraft Mandatory Service Bulletin SB 70– 

183, dated January 2010; and L’Hotellier 

Service Bulletin 863520–26–001, dated 

December 21, 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 SOCATA—Direction des 

Services—65921 Tarbes Cedex 9—France; 

telephone +33 (0)5 6241–7300, fax +33 (0)5 

62 41 76 54, or for North America: SOCATA 

NORTH AMERICA, 7501 South Airport 

Road, North Perry Airport (HWO), Pembroke 

Pines, Florida 33023; telephone: 954–893– 

1400; fax: 54–964–4141. For details on the 

fire extinguisher, contact: L’HOTELLIER, 4 

rue Henri Poincare ́, 92167 ANTONY Cedex, 

France; telephone +33(0) 1 46 66 08 08; fax 

+33(0) 1 46 66 23 24; e-mail: 

alain.dorneau@hs.utc.com. To obtain a copy 

of the referenced L’Hotellier service bulletin, 

e-mail: sylvie.laruffa@hs.utc.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 May 

19, 2010. 

John R. Colomy, 

Acting Manager, Small Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2010–12595 Filed 5–28–10; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2009–0866; Directorate 

Identifier 2009–NM–074–AD; Amendment 

39–16317; AD 2010–11–12] 

RIN 2120–AA64 

Airworthiness Directives; McDonnell 

Douglas Corporation Model MD–11 and 

MD–11F 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 Model MD–11 

and MD–11F airplanes. That AD 

currently requires a one-time inspection 

to determine if metallic transitions are 

installed on wire harnesses of the tail 

tank fuel transfer pumps, and to 

determine if damaged wires are present; 

and repair, if necessary. That AD also 

requires repetitive inspections of the 

repaired area; and a permanent 

modification of the wire harnesses if 

metallic transitions are not installed, 

which would terminate the repetitive 

inspections. This new AD requires 

modifying the case grounding for the 

alternate fuel pump of the tail tank, the 

leak detection thermal switch grounding 

for the number 2 engine, and wire braid 

grounding in the empennage and 

number 2 engine inlet. This AD also 

removes one airplane from the 

applicability of the existing AD. This 

AD results from reports that the wire 

assembly for the alternate fuel pump is 

missing a case ground wire, and the 

lightning protection wire braid for wire 

assemblies located in the empennage 

and number 2 engine inlet are grounded 

improperly. We are issuing this AD to 

prevent insufficient grounding of the 

fuel pump, which in combination with 

an electrical failure within the fuel 

pump and a compromised electrical 

bond could cause a fuel tank ignition, 

resulting in consequent fire or 

explosion. 

DATES: This AD becomes effective July 

6, 2010. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in the AD 

as of July 6, 2010. 

On January 18, 2000 (64 FR 69389, 

December 13, 1999), the Director of the 

Federal Register approved the 

incorporation by reference of certain 

other publications listed in the AD. 

ADDRESSES: For service information 

identified in this AD, contact Boeing 

Commercial Airplanes, Attention: Data 

& Services Management, 3855 

Lakewood Boulevard, MC D800–0019, 

Long Beach, California 90846–0001; 

telephone 206–544–5000, extension 2; 

fax 206–766–5683; e-mail 

dse.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: 

Samuel Lee, Aerospace Engineer, 

Propulsion Branch, ANM–140L, FAA, 

Los Angeles Aircraft Certification 


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Federal Register / Vol. 75, No. 104 / Tuesday, June 1, 2010 / Rules and Regulations 30275 

Office, 3960 Paramount Boulevard, 

Lakewood, California 90712–4137; 

telephone (562) 627–5262; fax (562) 

627–5210. 

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 99–25–14, amendment 

39–11457 (64 FR 69389, December 13, 

1999). The existing AD applies to 

certain Model MD–11 and MD–11F 

airplanes. That NPRM was published in 

the Federal Register on September 18, 

2009 (74 FR 47900). That NPRM 

proposed to continue to require a onetime inspection to determine if metallic 

transitions are installed on wire 

harnesses of the tail tank fuel transfer 

pumps, and to determine if damaged 

wires are present; and repair, if 

necessary. That NPRM also proposed to 

continue to require repetitive 

inspections of the repaired area; and a 

permanent modification of the wire 

harnesses if metallic transitions are not 

installed, which would terminate the 

repetitive inspections. That NPRM also 

proposed to require modifying the case 

grounding for the alternate fuel pump of 

the tail tank, the leak detection thermal 

switch grounding for the number 2 

engine, and wire braid grounding in the 

empennage and number 2 engine inlet. 

That NPRM also proposed to remove 

one airplane from the applicability of 

the existing AD. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. We 

considered the comment received from 

the commenter. The commenter, FedEx 

Express, agrees with the requirements of 

the proposed AD. 

Request To Change Proposed Costs of 

Compliance 

FedEx Express requests that the costs 

for concurrently required actions be 

included in the proposed Costs of 

Compliance. FedEx Express states that 

the estimated costs need to be revised 

since concurrent requirements are 

included in Boeing Alert Service 

Bulletin MD11–28A140, dated 

November 6, 2008, which is cited in the 

NPRM as the appropriate guidance for 

modifying the case grounding, leak 

detention thermal switch grounding, 

and wire braid grounding. That service 

bulletin specifies that McDonnell 

Douglas Service Bulletin MD11–28–102, 

Revision 01, dated June 23, 1999, must 

be done before or at the same time as 

Boeing Alert Service Bulletin MD11– 

28A140. 

FedEx Express states that McDonnell 

Douglas Service Bulletin MD11–28–102, 

Revision 01, dated June 23, 1999, 

constitutes terminating action for AD 

99–25–14, and it takes 28.8 hours for 

Group 1 (12 airplanes) and 40.4 hours 

for Group 2 (1 airplane). FedEx Express 

states that, considering all U.S.- 

registered airplanes are in Group 1 (9 

airplanes), this will cost $20,736 in 

labor with no cost for parts. 

FedEx Express states that Boeing Alert 

Service Bulletin MD11–28A140 

specifies that it takes 18.5 hours for 

Group 1 (12 airplanes) and 24.5 hours 

for Group 2 (1 airplane). FedEx Express 

asserts that, considering all U.S.- 

registered airplanes are in Group 1 (9 

airplanes), this will cost $13,320 for 

labor and $11,232 for parts. 

FedEx Express states that the 

proposed AD will cost approximately 

$34,056 in labor and $11,232 in parts 

with a total cost of $45,288. Therefore, 

FedEx Express asserts the estimated cost 

for the proposed AD should be stated as: 

Rework (required by AD 99–25–14) 

$20,736 and Modification (new 

proposed action) $24,552, resulting in a 

total fleet cost (U.S.-registered airplanes) 

of $45,288. 

We disagree with FedEx Express’s 

request to include McDonnell Douglas 

Service Bulletin MD11–28–102, 

Revision 01, dated June 23, 1999, in the 

Costs of Compliance section of this AD. 

The costs in AD 99–25–14 only specify 

the cost for the inspection, and not the 

modification. The modification 

specified in that service bulletin is an 

‘‘on-condition’’ requirement in existing 

AD 99–25–14. The modification is 

considered on-condition for airplanes 

that are not equipped with metallic 

transitions as specified in paragraph 

(g)(2) of this AD. The economic analysis 

of an AD is limited to the cost of actions 

that are actually required and it does not 

consider the costs of ‘‘on-condition’’ 

actions (that is, actions needed to 

correct an unsafe condition) because, 

regardless of AD direction, those actions 

would be required to correct an unsafe 

condition identified in an airplane and 

ensure operation of that airplane in an 

airworthy condition, as required by the 

Federal Aviation Regulations. We have 

not changed the final rule regarding this 

issue. 

Explanation of Change 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. 

Explanation of Change Made to Service 

Bulletin Citations 

We have revised this AD to provide 

full service bulletin citations throughout 

this AD. 

Conclusion 

We have carefully 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 have determined that 

these changes will neither increase the 

economic burden on any operator nor 

increase the scope of the AD. 

Explanation of Changes 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. 

We have revised the cost of parts from 

$80 to $0 in the section ‘‘Inspection 

(required by AD 99–25–14)’’ in this AD. 

In the NPRM, we inadvertently included 

a cost of $80 in the parts column of the 

‘‘Estimated Costs’’ table. 

Costs of Compliance 

There are about 13 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. 


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30276 Federal Register / Vol. 75, No. 104 / Tuesday, June 1, 2010 / Rules and Regulations 

ESTIMATED COSTS

Action Work hours 

Average 

labor rate 

per hour 

Parts Cost per airplane 

Number of 

U.S.- 

registered 

airplanes 

Fleet cost 

Inspection (required by AD 

99–25–14).

1 $85 $0 $85, per inspection cycle .. 9 $765, per inspection cycle. 

Modification (new required 

action).

16 85 1,248 $2,608 ............................... 9 $23,472. 

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 have 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 that this AD: 

(1) Is not a ‘‘significant regulatory 

action’’ under Executive Order 12866; 

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

DOT Regulatory Policies and Procedures 

(44 FR 11034, February 26, 1979); and 

(3) Will not have a significant 

economic impact, positive or negative, 

on a substantial number of small entities 

under the criteria of the Regulatory 

Flexibility Act. 

We prepared a regulatory evaluation 

of the estimated costs to comply with 

this AD and placed it in the AD docket. 

See the ADDRESSES section for a location 

to examine the regulatory evaluation. 

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 Federal Aviation 

Administration (FAA) amends § 39.13 

by removing amendment 39–11457 (64 

FR 69389, December 13, 1999) and by 

adding the following new airworthiness 

directive (AD): 

2010–11–12 McDonnell Douglas 

Corporation: Amendment 39–16317. 

Docket No. FAA–2009–0866; Directorate 

Identifier 2009–NM–074–AD. 

Effective Date 

(a) This AD becomes effective July 6, 2010. 

Affected ADs 

(b) This AD supersedes AD 99–25–14, 

Amendment 39–11457. 

Applicability 

(c) This AD applies to McDonnell Douglas 

Corporation Model MD–11 and MD–11F 

airplanes, certificated in any category, as 

identified in Boeing Alert Service Bulletin 

MD11–28A140, dated November 6, 2008. 

Subject 

(d) Air Transport Association (ATA) of 

America Code 28: Fuel. 

Unsafe Condition 

(e) This AD results from reports that the 

wire assembly for the alternate fuel pump is 

missing a case ground wire, and the lightning 

protection wire braid for wire assemblies 

located in the empennage and number 2 

engine inlet are grounded improperly. The 

Federal Aviation Administration is issuing 

this AD to prevent insufficient grounding of 

the fuel pump, which in combination with an 

electrical failure within the fuel pump and a 

compromised electrical bond could cause a 

fuel tank ignition, resulting in consequent 

fire or explosion. 

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. 

Restatement of Requirements of AD 99–25– 

14 with No Changes 

Inspection and Corrective Actions 

(g) Within 30 days after January 18, 2000 

(the effective date of AD 99–25–14), perform 

a one-time visual inspection of the wire 

harnesses of the tail tank fuel transfer pumps 

to determine if metallic transitions are 

installed, and to determine if damaged wires 

are present, in accordance with McDonnell 

Douglas Alert Service Bulletin MD11– 

28A101, dated August 24, 1998. 

(1) If all metallic transitions are installed, 

no further action is required by paragraph (g) 

of this AD. 

(2) If metallic transitions are not installed, 

accomplish the following: 

(i) Prior to further flight, accomplish the 

temporary repair in accordance with 

condition 2 of McDonnell Douglas Alert 

Service Bulletin MD11–28A101, dated 

August 24, 1998; 

(ii) Repeat the visual inspection thereafter 

at intervals not to exceed 2 years; and 

(iii) Within 5 years after January 18, 2000, 

permanently modify the wire harnesses in 

accordance with McDonnell Douglas Service 

Bulletin MD11–28–102, Revision 01, dated 

June 23, 1999. Accomplishment of this 

modification constitutes terminating action 

for the repetitive inspection requirements of 

this AD. 

Note 1: Modification of the wire harnesses 

accomplished prior to January 18, 2000, in 

accordance with McDonnell Douglas Service 

Bulletin MD11–28–102, dated January 29, 

1999, is considered acceptable for 

compliance with the modification required 

by paragraph (g)(2)(iii) of this AD. 

New Requirements of This AD 

Modification 

(h) Within 72 months after the effective 

date of this AD, modify the case grounding 

for the alternate fuel pump of the tail tank, 

the leak detection thermal switch grounding 

for the number 2 engine, and wire braid 

grounding in the empennage and number 2 

engine inlet, in accordance with the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin MD11–28A140, dated 

November 6, 2008. 

Alternative Methods of Compliance 

(AMOCs) 

(i)(1) The Manager, Los Angeles Aircraft 

Certification Office (ACO), FAA, has the 

authority to approve AMOCs for this AD, if 

requested using the procedures found in 14 


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Federal Register / Vol. 75, No. 104 / Tuesday, June 1, 2010 / Rules and Regulations 30277 

CFR 39.19. Send information to ATTN: 

Samuel Lee, Aerospace Engineer, Propulsion 

Branch, ANM–140L, FAA, Los Angeles ACO, 

3960 Paramount Boulevard, Lakewood, 

California 90712–4137; telephone (562) 627– 

5262; fax (562) 627–5210. 

(2) To request a different method of 

compliance or a different compliance time 

for this AD, follow the procedures in 14 CFR 

39.19. Before using any approved AMOC on 

any airplane to which the AMOC applies, 

notify your principal maintenance inspector 

(PMI) or principal avionics inspector (PAI), 

as appropriate, or lacking a principal 

inspector, your local Flight Standards District 

Office. The AMOC approval letter must 

specifically reference this AD. 

Material Incorporated by Reference 

(j) You must use the applicable service 

information contained in Table 1 of this AD 

to do the actions required by this AD, unless 

the AD specifies otherwise. 

TABLE 1—ALL MATERIAL INCORPORATED BY REFERENCE

Document Revision Date 

Boeing Alert Service Bulletin MD11–28A140 .................................................................................. Original ...................... November 6, 2008. 

McDonnell Douglas Alert Service Bulletin MD11–28A101. ............................................................. Original ...................... August 24, 1998. 

McDonnell Douglas Service Bulletin MD11–28–102 ....................................................................... Revision 01 ................ June 23, 1999. 

(1) The Director of the Federal Register 

approved the incorporation by reference of 

Boeing Alert Service Bulletin MD11–28A140, 

dated November 6, 2008, under 5 U.S.C. 

552(a) and 1 CFR part 51. 

(2) The Director of the Federal Register 

previously approved the incorporation by 

reference of McDonnell Douglas Alert Service 

Bulletin MD11–28A101, dated August 24, 

1998; and McDonnell Douglas Service 

Bulletin MD11–28–102, Revision 01, dated 

June 23, 1999; on January 18, 2000 (64 FR 

69389, December 13, 1999). 

(3) For service information identified in 

this AD, contact Boeing Commercial 

Airplanes, Attention: Data & Services 

Management, 3855 Lakewood Boulevard, MC 

D800–0019, Long Beach, California 90846– 

0001; telephone 206–544–5000, extension 2; 

fax 206–766–5683; e-mail 

dse.boecom@boeing.com; Internet https:// 

www.myboeingfleet.com. 

(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. 

(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. 

Issued in Renton, Washington, on May 14, 

2010. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2010–12667 Filed 5–28–10; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2010–0175; Directorate 

Identifier 2009–NM–187–AD; Amendment 

39–16319; AD 2010–11–14] 

RIN 2120–AA64 

Airworthiness Directives; Empresa 

Brasileira de Aeronautica S.A. 

(EMBRAER) Model ERJ 190–100 STD, 

–100 LR, –100 IGW, –200 STD, –200 LR, 

and –200 IGW 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 ERJ 190 airplane full scale fatigue 

test, cracks were found in some structural 

components of the airplane. Analysis of these 

cracks resulted in modifications on the 

airplane Airworthiness Limitation Items 

(ALI), to include new inspections tasks or 

modification of existing ones and its 

respective thresholds and intervals. 

Failure to inspect these components 

according to the new tasks, thresholds and 

intervals could prevent a timely detection of 

fatigue cracks. Undetected fatigue cracks in 

these areas could adversely affect the 

structural integrity of these airplanes. 

* * * * * 

We are issuing this AD to require 

actions to correct the unsafe condition 

on these products. 

DATES: This AD becomes effective July 

6, 2010. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in this AD 

as of July 6, 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: 

Kenny Kaulia, Aerospace Engineer, 

International Branch, ANM–116, 

Transport Airplane Directorate, FAA, 

1601 Lind Avenue SW., Renton, 

Washington 98057–3356; telephone 

(425) 227–2848; 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 March 4, 2010 (75 FR 9814). 

That NPRM proposed to correct an 

unsafe condition for the specified 

products. The MCAI states: 

During ERJ 190 airplane full scale fatigue 

test, cracks were found in some structural 

components of the airplane. Analysis of these 

cracks resulted in modifications on the 

airplane Airworthiness Limitation Items 

(ALI), to include new inspections tasks or 

modification of existing ones and its 

respective thresholds and intervals. 

Failure to inspect these components 

according to the new tasks, thresholds and 

intervals could prevent a timely detection of 

fatigue cracks. Undetected fatigue cracks in 

these areas could adversely affect the 

structural integrity of these airplanes. 

* * * * * 

The corrective action is revising the 

Airworthiness Limitations Section of 

the Instructions for Continued 

Airworthiness to incorporate new and 

modified structural inspections. You 


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