Federal Register / Vol. 72, No. 153 / Thursday, August 9, 2007 / Rules and Regulations 44731 

(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 appropriate principal inspector 

(PI) in the FAA Flight Standards District 

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

FSDO. 

(3) An AMOC that provides an acceptable 

level of safety may be used for any repair 

required by this AD, if it is approved by an 

Authorized Representative for the Boeing 

Commercial Airplanes Delegation Option 

Authorization Organization who has been 

authorized by the Manager, Seattle ACO, to 

make those findings. For a repair method to 

be approved, the repair must meet the 

certification basis of the airplane. 

(4) AMOCs approved previously in 

accordance with AD 2001–14–22, are 

approved as AMOCs for the corresponding 

provisions of paragraphs (f) and (j) of this 

AD. 

(5) AMOCS approved previously in 

accordance with AD 2006–12–12, are 

approved as alternative methods of 

compliance with this AD. 

Material Incorporated by Reference 

(m) You must use Boeing Alert Service 

Bulletin 747–53A2451, including Appendix 

A, dated October 5, 2000; or Boeing Alert 

Service Bulletin 747–53A2451, Revision 1, 

dated November 10, 2005; as applicable, to 

perform the actions that are required by this 

AD, unless the AD specifies otherwise. 

(1) On July 17, 2006 (71 FR 33595, June 12, 

2006), the Director of the Federal Register 

approved the incorporation by reference of 

Boeing Alert Service Bulletin 747–53A2451, 

Revision 1, dated November 10, 2005. 

(2) On August 30, 2001 (66 FR 38891, July 

26, 2001), the Director of the Federal Register 

approved the incorporation by reference of 

Boeing Alert Service Bulletin 747–53A2451, 

including Appendix A, dated October 5, 

2000. 

(3) Contact Boeing Commercial Airplanes, 

P.O. Box 3707, Seattle, Washington 98124–

2207, for a copy of this service information. 

You may review copies at the FAA, 

Transport Airplane Directorate, 1601 Lind 

Avenue SW., Renton, Washington; 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/federal-register/cfr/ibrlocations.html. 

Issued in Renton, Washington, on July 30, 

2007. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. E7–15416 Filed 8–8–07; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2007–27741; Directorate 

Identifier 2006–NM–261–AD; Amendment 

39–15141; AD 2007–16–02] 

RIN 2120–AA64 

Airworthiness Directives; Airbus Model 

A330–201, –202, –203, –223, –243, 

–301, –321, –322, –323, –341, –342, and 

–343 Airplanes; and Model A340–200 

and –300 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) 

issued by an airworthiness authority of 

another country to identify and correct 

an unsafe condition on an aviation 

product. The MCAI describes the unsafe 

condition as keel beam rupture, which 

affects the structural integrity of the 

area. We are issuing this AD to require 

actions to correct the unsafe condition 

on these products. 

DATES: This AD becomes effective 

September 13, 2007. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in this AD 

as of September 13, 2007. 

ADDRESSES: You may examine the AD 

docket on the Internet at http:// 

dms.dot.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: Tim 

Backman, Aerospace Engineer, 

International Branch, ANM–116, FAA, 

Transport Airplane Directorate, 1601 

Lind Avenue SW., Renton, Washington 

98057–3356; telephone (425) 227–2797; 

fax (425) 227–1149. 

SUPPLEMENTARY INFORMATION: 

Discussion 

The FAA is implementing a new 

process for streamlining the issuance of 

ADs related to MCAI. This streamlined 

process will allow us to adopt MCAI 

safety requirements in a more efficient 

manner and will reduce safety risks to 

the public. This process continues to 

allow all FAA AD issuance processes to 

meet legal, economic, Administrative 

Procedure Act, and Federal Register 

requirements. We also continue to meet 

our technical decision-making 

responsibilities to identify and correct 

unsafe conditions on U.S.-certificated 

products. 

This AD references the MCAI and 

related service information that we 

considered in forming the engineering 

basis to correct the unsafe condition. 

The AD contains text copied from the 

MCAI and for this reason might not 

follow our plain language principles. 

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 30, 2007 (72 FR 

15067). That NPRM proposed to require 

a repetitive special detailed inspection 

on the horizontal flange of the keel 

beam in the area of the first fastener 

hole aft of FR (frame) 40, follow-up 

actions (further inspections, installation 

of new fasteners, and sealing the 

fasteners), and repair if necessary. The 

MCAI states that during the A330 and 

A340 aircraft fatigue test, cracks 

appeared on the right and left sides 

between the crossing area of the keel 

beam fitting and the front spar on the 

center wing box (CWB). This situation if 

not corrected can lead in the worst case 

to keel beam rupture, which affects the 

structural integrity of the area. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. We 

considered the comment received. 

Request To Refer to Revised MCAI 

Airbus requests we refer to European 

Aviation Safety Agency (EASA) 

Airworthiness Directive 2006–0315 R1, 

dated October 26, 2006, in the AD. (We 

referred to EASA Airworthiness 

Directive 2006–0315, dated October 13, 

2006, in the NPRM.) Airbus notes that 

Revision 1 of the EASA airworthiness 

directive adds an optional terminating 

action for the repetitive inspections. 

We agree with Airbus, and have 

revised this AD to refer to Revision 1 of 

the EASA Airworthiness Directive. 

Revision 1 refers to the following Airbus 

Service Bulletins as the appropriate 

sources of service information for doing 

the optional terminating action: A330–

57–3090, dated March 27, 2006; and 

A340–57–4098, dated March 27, 2006. 

The modification can be done only on 

airplanes without Airbus Modification 

41652. 

The optional terminating action is a 

modification that involves 

disconnecting one or more fasteners 

from the keel beam/bottom skin panel 


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junction, removing two adjacent 

fasteners in order to perform cold 

working, and installing interference fit 

fasteners. The modification also 

involves inspections and repairing any 

cracking detected during the 

modification; in some instances the 

repair for cracking or for any bushing 

that has a diameter beyond certain 

limits specified in the service bulletin is 

contacting Airbus for repair 

instructions. We have added paragraph 

(e)(6) to this AD, and revised paragraph 

(d) of this AD to include the optional 

terminating action. We have revised 

paragraph (g) of this AD to refer to 

Revision 1 of the MCAI. 

Explanation of Change to Paragraph 

(c)(3) ‘‘Applicability’’

When we issued the NPRM we noted 

in paragraph (c)(3) that we were 

considering rulemaking regarding EASA 

airworthiness directive 2006–0314. 

EASA airworthiness directive 2006–

0314 applies to Model A340–200 and 

–300 series airplanes repaired in 

accordance with certain Airbus repair 

drawings, and paragraph (c)(3) of the 

NPRM notes that those airplanes are not 

affected by the current action. We have 

since issued AD 2007–12–08, 

amendment 39–15086 (72 FR 31171, 

June 6, 2007), which is the parallel FAA 

AD to EASA airworthiness directive 

2006–0314. We have changed paragraph 

(c)(3) of this AD to refer to AD 2007–12–

08. 

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 a U.S. 

court of law. 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 

described in a separate paragraph of the 

AD. These requirements, if any, take 

precedence over the actions copied from 

the MCAI. 

Costs of Compliance 

We estimate that this AD will affect 

about 9 products of U.S. registry. We 

also estimate that it will take about 12 

work-hours per product to comply with 

this AD. The average labor rate is $80 

per work-hour. Required parts will cost 

about $382 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 

$12,078, or $1,342 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 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. 

Examining the AD Docket 

You may examine the AD docket on 

the Internet at http://dms.dot.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: 

2007–16–02 Airbus: Amendment 39–15141. 

Docket No. FAA–2007–27741; 

Directorate Identifier 2006–NM–261–AD. 

Effective Date 

(a) This airworthiness directive (AD) 

becomes effective September 13, 2007. 

Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to the airplanes 

identified in paragraphs (c)(1) and (c)(2) of 

this AD; certificated in any category; except 

as provided by paragraph (c)(3) of this AD. 

(1) Airbus Model A330–201, –202, –203, 

–223, –243, –301, –321, –322, –323, –341, 

–342, and –343 airplanes, all serial numbers, 

except those on which Airbus modification 

49202 has been embodied in production, or 

Airbus Service Bulletin A330–57–3090 has 

been embodied in service. 

(2) Airbus Model A340–200 and –300 

series airplanes, all certified models, all 

serial numbers, except those on which 

Airbus modification 49202 has been 

embodied in production or Airbus Service 

Bulletin A340–57–4098 has been embodied 

in service. 

(3) This AD does not apply to Model 

A340–200 and –300 series airplanes repaired 


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in accordance with Airbus Repair Drawing 

R57115053, R57115051, or R57115047 

(installation of titanium doubler). These 

airplanes are covered by European Aviation 

Safety Agency (EASA) airworthiness 

directive 2006–0314, dated October 13, 2006. 

On May 25, 2007, we issued AD 2007–12–08, 

amendment 39–15086 (72 FR 31171, June 6, 

2007), which is the parallel FAA AD to EASA 

airworthiness directive 2006–0314. 

Reason 

(d) The mandatory continuing 

airworthiness information (MCAI) states that 

during the A330 and A340 aircraft fatigue 

test, cracks appeared on the right and left 

sides between the crossing area of the keel 

beam fitting and the front spar on the center 

wing box (CWB). This situation if not 

corrected can lead in the worst case to keel 

beam rupture which affects the structural 

integrity of the area. In order to maintain the 

structural integrity of the aircraft, the MCAI 

requires a repetitive special detailed 

inspection on the horizontal flange of the 

keel beam in the area of the first fastener hole 

aft of FR (frame) 40, follow-up actions, and 

repair if necessary. The MCAI also includes 

an optional terminating action for the 

repetitive inspections. 

Actions and Compliance 

(e) Unless already done, do the following 

actions. 

(1) Within the mandatory threshold (flight 

cycles or flight hours) mentioned in the 

paragraph 1.E.(2) of Airbus Service Bulletin 

A340–57–4089, Revision 02; or A330–57–

3081, Revision 02; both dated January 24, 

2006, depending on the configuration of the 

aircraft model; or within 3 months after the 

effective date of this AD; whichever occurs 

later: Carry out the NDT (non-destructive 

test) inspection of the hole(s) of the 

horizontal flange of the keel beam located on 

FR 40 datum on RH (right-hand) and/or LH 

(left-hand) side of the fuselage, in accordance 

with the instructions of Airbus Service 

Bulletin A340–57–4089, Revision 02; or 

A330–57–3081, Revision 02; as applicable. 

Inspection in accordance with Airbus A330/ 

A340 Technical Disposition F57D03012810, 

Issue B, dated August 18, 2003; or 582.0651/ 

2002, Issue A, dated October 17, 2002; 

satisfies the inspection requirements for the 

first rotating probe inspection which is 

specified at the inspection threshold of this 

AD. 

Note 1: In order to prevent large repairs or 

heavy maintenance, Airbus recommends to 

perform the above inspection according to 

recommended thresholds mentioned in 

paragraph 1.E.(2) of Airbus Service Bulletin 

A340–57–4089, Revision 02; or Airbus 

Service Bulletin A330–57–3081, Revision 02; 

both dated January 24, 2006. 

(2) In case of any crack finding, before 

further flight, contact Airbus in order to get 

repair instructions before next flight, and 

repair before further flight. 

(3) Should no crack be detected: 

(i) Before further flight: Follow up the 

actions indicated in the flow charts, figure 7, 

8, or 9, of Airbus Service Bulletin A340–57–

4089, including Appendix 01, Revision 02, 

dated January 24, 2006; or figure 5, 6, or 7, 

of Airbus Service Bulletin A330–57–3081, 

including Appendix 01, Revision 02, dated 

January 24, 2006; in accordance with the 

instructions of the applicable service 

bulletin. 

(ii) Within 30 days after the effective date 

of this AD, or within 30 days after doing the 

inspection required by paragraph (e)(1) of 

this AD, whichever occurs later: Send the 

report of actions carried out in paragraph 

(e)(3)(i) of this AD to Airbus. 

(iii) Renew the inspection at mandatory 

intervals given in paragraph 1.E.(2) of Airbus 

Service Bulletin A340–57–4089, Revision 02, 

dated January 24, 2006; or Airbus Service 

Bulletin A330–57–3081, Revision 02, dated 

January 24, 2006; as applicable; in 

accordance with the instructions of Service 

Bulletin A340–57–4089, Revision 02, or 

Service Bulletin A330–57–3081, Revision 02; 

as applicable, and send the inspection results 

to Airbus. 

Note 2: In order to prevent large repairs or 

heavy maintenance, Airbus recommends to 

perform the above repetitive inspection 

according to recommended intervals 

mentioned in paragraph 1.E.(2) of Airbus 

Service Bulletin A340–57–4089, Revision 02, 

dated January 24, 2006; or Airbus Service 

Bulletin A330–57–3081, Revision 02, dated 

January 24, 2006. 

(4) Upon detection of a crack during a 

repetitive inspection, before further flight, 

contact Airbus to get repair instructions, and 

repair before further flight. 

(5) No additional work is required for 

aircraft inspected in accordance with the 

instructions of Airbus Service Bulletin A330–

57–3081, dated October 30, 2003, or Revision 

01, dated May 18, 2004; or Airbus Service 

Bulletin A340–57–4089, dated October 30, 

2003, or Revision 01, dated March 2, 2004. 

Nevertheless, the operators must check that 

their inspection program is in accordance 

with paragraph 1.E.(2) of Airbus Service 

Bulletin A340–57–4089, Revision 02, dated 

January 24, 2006; or Airbus Service Bulletin 

A330–57–3081, Revision 02, dated January 

24, 2006; as applicable; for the repetitive 

inspection. 

(6) For aircraft on which Airbus 

Modification 41652 is not embodied: When 

the aircraft has been modified in accordance 

with Airbus Service Bulletin A330–57–3090, 

dated March 27, 2006; or Airbus Service 

Bulletin A340–57–4098, dated March 27, 

2006; as applicable; the repetitive inspections 

required by this AD are cancelled. In case of 

any crack finding during the modification: 

Where the applicable service bulletin 

specifies to contact Airbus, before further 

flight, contact Airbus to get repair 

instructions, and repair. 

FAA AD Differences 

Note: This AD differs from the MCAI and/ 

or service information as follows. The MCAI 

did not have a required action if cracks are 

found during a repetitive inspection. This AD 

requires contacting Airbus for repair 

instructions and repairing before further 

flight. 

Other FAA AD Provisions 

(f) The following provisions also apply to 

this AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, 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: Tim 

Backman, Aerospace Engineer, International 

Branch, ANM–116, FAA, Transport Airplane 

Directorate, 1601 Lind Avenue SW., Renton, 

Washington 98057–3356. 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, 

the Office of Management and Budget (OMB) 

has approved the information collection 

requirements and has assigned OMB Control 

Number 2120–0056. 

Related Information 

(g) Refer to MCAI EASA Airworthiness 

Directive 2006–0315 R1, dated October 26, 

2006, and the service information listed in 

Table 1 of this AD, for related information. 

TABLE 1.—RELATED SERVICE INFORMATION

Airbus Service Bulletin Revision level Date 

A330–57–3081 ............................................................................................................................................... 02 .................... January 24, 2006. 

A330–57–3090 ............................................................................................................................................... Original ........... March 27, 2006. 

A340–57–4089 ............................................................................................................................................... 02 .................... January 24, 2006. 

A340–57–4098 ............................................................................................................................................... Original ........... March 27, 2006. 


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Material Incorporated by Reference 

(h) You must use the applicable service 

information specified in Table 2 of this AD 

to do the actions required by this AD, unless 

the AD specifies otherwise. If you 

accomplish the optional terminating 

modification specified in this AD, you must 

use the applicable service information 

specified in Table 3 of this AD. 

TABLE 2.—REQUIRED MATERIAL INCORPORATED BY REFERENCE

Airbus Service Bulletin Revision Date 

A330–57–3081, including Appendix 01 ...................................................................................................... 02 January 24, 2006. 

A340–57–4089, including Appendix 01 ...................................................................................................... 02 January 24, 2006. 

TABLE 3.—OPTIONAL MATERIAL

INCORPORATED BY REFERENCE

Airbus Service Bulletin Date 

A330–57–3090 ................. March 27, 2006. 

A340–57–4098 ................. March 27, 2006. 

(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, 1 Rond Point 

Maurice Bellonte, 31707 Blagnac Cedex, 

France. 

(3) You may review copies at the FAA, 

Transport Airplane Directorate, 1601 Lind 

Avenue SW., Renton, Washington; 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/federal-register/cfr/ibrlocations.html. 

Issued in Renton, Washington, on July 24, 

2007. 

Stephen P. Boyd, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. E7–14866 Filed 8–8–07; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2007–28094; Directorate 

Identifier 2006–NM–258–AD; Amendment 

39–15148; AD 2007–16–09] 

RIN 2120–AA64 

Airworthiness Directives; Empresa 

Brasileira de Aeronautica S.A. 

(EMBRAER) Model ERJ 170 Airplanes 

and Model ERJ 190 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 all EMBRAER Model 

ERJ 170–100 LR, –100 STD, –100 SE, 

and –100 SU airplanes. That AD 

currently requires repetitively replacing 

the low-stage check valve and 

associated seals of the right-hand engine 

bleed system. This new AD adds new 

airplanes to that existing requirement. 

For all airplanes, this AD also requires 

repetitively replacing the low-stage 

check valve and associated seals of the 

left-hand engine bleed system with a 

new check valve and new seals. This 

AD results from a report that an engine 

shut down during flight due to the 

failure of the low-stage check valve to 

close. We are issuing this AD to prevent 

failure of the low-stage check valve, 

which could result in an engine shutting 

down during flight. 

DATES: This AD becomes effective 

September 13, 2007. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in the AD 

as of September 13, 2007. 

On November 29, 2005 (70 FR 69075, 

November 14, 2005), the Director of the 

Federal Register approved the 

incorporation by reference of a certain 

service bulletin. 

ADDRESSES: You may examine the AD 

docket on the Internet at http:// 

dms.dot.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. 

Contact Empresa Brasileira de 

Aeronautica S.A. (EMBRAER), P.O. Box 

343–CEP 12.225, Sao Jose dos Campos—

SP, Brazil, for service information 

identified in this AD. 

FOR FURTHER INFORMATION CONTACT: 

Todd Thompson, Aerospace Engineer, 

International Branch, ANM–116, FAA, 

Transport Airplane Directorate, 1601 

Lind Avenue, SW., Renton, Washington 

98057–3356; telephone (425) 227–1175; 

fax (425) 227–1149. 

SUPPLEMENTARY INFORMATION: 

Examining the Docket 

You may examine the AD docket on 

the Internet at http://dms.dot.gov or in 

person at the Docket Operations office 

between 9 a.m. and 5 p.m., Monday 

through Friday, except Federal holidays. 

The Docket Operations office (telephone 

(800) 647–5527) is located on the 

ground floor of the West Building at the 

DOT street address stated in the 

ADDRESSES section. 

Discussion 

The FAA issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to include an AD that 

supersedes AD 2005–23–14, amendment 

39–14372 (70 FR 69075, November 14, 

2005). The existing AD applies to all 

EMBRAER Model ERJ 170–100 LR, –100 

STD, –100 SE, and –100 SU airplanes. 

That NPRM was published in the 

Federal Register on May 8, 2007 (72 FR 

26008). That NPRM proposed to 

continue to require repetitively 

replacing the low-stage check valve and 

associated seals of the right-hand (RH) 

engine bleed system. That NPRM also 

proposed to add new airplanes to that 

existing requirement. For all airplanes, 

that NPRM also proposed to require 

repetitively replacing the low-stage 

check valve and associated seals of the 

left-hand (LH) engine bleed system with 

a new check valve and new seals. 

Comments 

We provided the public the 

opportunity to participate in the 

development of this AD. No comments 

have been received on the NPRM or on 

the determination of the cost to the 

public. 

Changes to This AD 

We have reviewed Revision 01 of 

EMBRAER Service Bulletin 190–36–

0004, dated November 14, 2006, and 

have determined that the 

accomplishment instructions of 

Revision 01 are the same as those in the 

original issue of the service bulletin. In 

the NPRM, we referred to the original 

issue of EMBRAER Service Bulletin 

190–36–0004, dated October 18, 2006, 

as the appropriate source of service 

information for replacing the low-stage 

check valves and associated seals of the 

RH and LH engine bleed system, on 

Model ERJ 190–100 STD, –100 LR, and 

–100 IGW airplanes. Therefore, we have 

revised paragraphs (j) and (k) of this AD 

to also refer to Revision 01 of EMBRAER 

Service Bulletin 190–36–0004, dated 

November 14, 2006, as an appropriate 

source of service information. We have 


jlentini on PROD1PC65 with RULES