Federal Register / Vol. 70, No. 206 / Wednesday, October 26, 2005 / Rules and Regulations 61729 

Effective Date 

(a) This AD becomes effective November 

30, 2005. 

Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to Boeing Model 747–

100, 747–100B, 747–100B SUD, 747–200B, 

747–200C, 747–200F, 747–300, 747SR, and 

747SP series airplanes, certificated in any 

category; as identified in Boeing Alert 

Service Bulletin 747–53A2508, dated August 

19, 2004. 

Unsafe Condition 

(d) This AD was prompted by reports of 

cracking at the upper aft corner of the cutout 

for main entry door number 1 in the station 

488 frame web. We are issuing this AD to 

detect and correct cracks in the frame web. 

These cracks could cause the frame to break 

and lead to rapid decompression of the 

airplane. 

Compliance 

(e) You are responsible for having the 

actions required by this AD performed within 

the compliance times specified, unless the 

actions have already been done. 

Initial Inspections 

(f) Before the accumulation of 16,000 total 

flight cycles, or within 1,000 flight cycles 

after the effective date of this AD, whichever 

occurs later, do a high frequency eddy 

current (HFEC) inspection and a detailed 

inspection of the station 488 frame web, by 

doing all of the actions specified in the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin (ASB) 747–53A2508, dated 

August 19, 2004; except as provided by 

paragraph (h) or (j) of this AD. 

Repetitive Inspections 

(g) If no crack is found during the 

inspections required by paragraph (f) of this 

AD, do the applicable actions specified in 

paragraph (g)(1) or (g)(2) of this AD. 

(1) For airplanes identified in the service 

bulletin as Groups 1 and 2: Repeat the 

detailed inspection required by paragraph (f) 

of this AD at intervals not to exceed 3,000 

flight cycles. 

(2) For airplanes identified in the service 

bulletin as Group 3, do the actions specified 

in either paragraph (g)(2)(i) or (g)(2)(ii) of this 

AD. 

(i) Repeat the detailed inspection required 

by paragraph (f) of this AD thereafter at 

intervals not to exceed 1,500 flight cycles. 

(ii) Within 1,500 flight cycles after the 

inspections required by paragraph (f) of this 

AD, perform a HFEC inspection for cracks of 

the frame web between the upper door sill 

and door stop number 8 in accordance with 

the method referenced in Figure 3 or Figure 

4 of the Accomplishment Instructions of the 

service bulletin. Repeat the HFEC inspection 

thereafter at intervals not to exceed 3,000 

flight cycles. 

Repairs 

(h) If any crack in the main entry door 

frame web is found during any inspection 

required by this AD: Before further flight, 

perform repairs—including an open-hole 

HFEC inspection of the frame inner chord—

in accordance with the Accomplishment 

Instructions of Boeing ASB 747–53A2508, 

dated August 19, 2004. Where the service 

bulletin specifies to contact Boeing for 

appropriate action: Before further flight, 

repair the door frame web and any frame 

chord damage using a method approved in 

accordance with paragraph (k) of this AD. 

Note 1: Boeing ASB 747–53A2508, dated 

August 19, 2004, references the Boeing 

Structural Repair Manual as an additional 

source of service information to comply with 

the intent of paragraph (h) this AD. 

Termination of Repeat Inspections 

(i) For the repaired frame web only, 

accomplishing the door frame web repair 

required by paragraph (h) of this AD ends the 

repetitive inspections required by paragraph 

(g) of this AD. 

Credit for Actions Accomplished Using 

Alternative ADs 

(j)(1) If the frame inner chord replacement 

required by AD 90–06–06, amendment 39–

6490, (which identifies Boeing Service 

Bulletin 747–53–2272, as listed in Boeing 

Document No. D6–35999, dated March 31, 

1989, as a source of service information) is 

accomplished concurrently with the repair of 

the station 488 door frame web specified by 

paragraph (h) of this AD, the open-hole HFEC 

inspection required by paragraph (h) of this 

AD is not required for the new frame inner 

chord. 

(2) Accomplishing the repetitive detailed 

inspections of the station 488 frame required 

by paragraph (f) of AD 2005–20–30, 

amendment 39–14327, or paragraph (f) of AD 

2005–08–01, amendment 39–14053, satisfies 

the requirements for the corresponding 

repetitive detailed inspections described by 

paragraphs (g)(1) and (g)(2)(i) of this AD, 

provided those inspections are performed at 

intervals corresponding with the applicable 

intervals required by this AD. 

Alternative Methods of Compliance 

(AMOCs) 

(k)(1) The Manager, Seattle ACO, FAA, has 

the authority to approve AMOCs for this AD, 

if requested in accordance with the 

procedures found in 14 CFR 39.19. 

(2) 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 DOA 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, and the approval must specifically 

refer to this AD. 

(3) Before using any AMOC approved in 

accordance with 14 CFR 39.19 on any 

airplane to which the AMOC applies, notify 

the appropriate principal inspector in the 

FAA Flight Standards Certificate Holding 

District Office. 

Material Incorporated by Reference 

(1) You must use Boeing Alert Service 

Bulletin 747–53A2508, dated August 19, 

2004, to perform the actions that are required 

by this AD, unless the AD specifies 

otherwise. The Director of the Federal 

Register approves the incorporation by 

reference of this document in accordance 

with 5 U.S.C. 552(a) and 1 CFR part 51. To 

get copies of the service information, contact 

Boeing Commercial Airplanes, P.O. Box 

3707, Seattle, Washington 98124–2207. To 

view the AD docket, go to the Docket 

Management Facility, U.S. Department of 

Transportation, 400 Seventh Street SW., 

room PL–401, Nassif Building, Washington, 

DC. To review copies of the service 

information, go to the National Archives and 

Records Administration (NARA). For 

information on the availability of this 

material at the 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 October 

18, 2005. 

Kevin M. Mullin, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 05–21293 Filed 10–25–05; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2004–18564; Directorate 

Identifier 2004–NM–16–AD; Amendment 39–

14352; AD 2005–22–08] 

RIN 2120–AA64 

Airworthiness Directives; Empresa 

Brasileira de Aeronautica S.A. 

(EMBRAER) Model EMB–135BJ, 

–135ER, –135KE, –135KL, –135LR, 

–145, –145ER, –145MR, –145LR, 

–145XR, –145MP, and –145EP 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: The FAA is adopting a new 

airworthiness directive (AD) for certain 

EMBRAER airplane models as identified 

above. This AD requires modifying the 

total air temperature (TAT) sensor 

heating system. This AD also allows 

replacing the fully automated digital 

electronic control (FADEC) assemblies 

with new or modified assemblies as an 

additional means of compliance. This 

AD results from a report indicating that 

the FADEC unit failed to compensate for 

ice accretion on the engine fan blades 

due to a false temperature signal from 

the TAT sensor to the FADEC. We are 

issuing this AD to prevent failure of the 

TAT sensor, which could result in 

61730 Federal Register / Vol. 70, No. 206 / Wednesday, October 26, 2005 / Rules and Regulations 

insufficient thrust to take off or (if 

coupled with the loss of an engine 

during takeoff) to abort the takeoff in a 

safe manner, and consequent reduced 

controllability of the airplane. 

DATES: This AD becomes effective 

November 30, 2005. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in the AD 

as of November 30, 2005. 

ADDRESSES: You may examine the AD 

docket on the Internet at http:// 

dms.dot.gov or in person at the Docket 

Management Facility, U.S. Department 

of Transportation, 400 Seventh Street, 

SW., Nassif Building, room PL–401, 

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 

98055–4056; 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 Management 

Facility office between 9 a.m. and 5 

p.m., Monday through Friday, except 

Federal holidays. The Docket 

Management Facility office (telephone 

(800) 647–5227) is located on the plaza 

level of the Nassif Building at the street 

address stated in the ADDRESSES section. 

Discussion 

The FAA issued a supplemental 

notice of proposed rulemaking (NPRM) 

to amend 14 CFR part 39 to include an 

AD that would apply to certain 

EMBRAER Model EMB–135BJ, –135ER, 

–135KE, –135KL, –135LR, –145, 

–145ER, –145MR, –145LR, –145XR, 

–145MP, and –145EP airplanes. That 

supplemental NPRM was published in 

the Federal Register on August 17, 2005 

(70 FR 48339). That supplemental 

NPRM proposed to require modifying 

the total air temperature (TAT) sensor 

heating system. That supplemental 

NPRM also allows for replacing the fully 

automated digital electronic control 

(FADEC) unit assemblies with new or 

modified assemblies as an additional 

means of compliance. 

New Relevant Service Information 

EMBRAER has issued Service Bulletin 

145–30–0028, Revision 10, dated March 

22, 2005. Paragraph (f) of the 

supplemental NPRM refers to 

EMBRAER Service Bulletin 145–30–

0028, Revision 09, dated March 1, 2004, 

as the appropriate source of service 

information for modifying the TAT 

sensor heating system. The applicability 

statement of the supplemental NPRM 

also refers to EMBRAER Service 

Bulletin 145–30–0028, Revision 09, as 

the source in which affected airplanes 

are identified. Revision 10 of the service 

bulletin includes minor editorial 

revisions, but no substantive changes. 

Therefore, we have revised the 

applicability statement and paragraph 

(f) of this AD to refer to EMBRAER 

Service Bulletin 145–30–0028, Revision 

10. We have also revised paragraph (g) 

of this AD to give credit for 

modifications done before the effective 

date of this AD in accordance with 

Revision 09. 

Comments 

We provided the public the 

opportunity to participate in the 

development of this AD. We have 

considered the comments received. 

Support for the Supplemental NPRM 

One commenter supports the intent of 

the supplemental NPRM. 

Request To Add Additional Means of 

Compliance 

The airplane manufacturer comments 

that it has recently approved FADEC 

software version 8.0. (Paragraph (h) of 

the supplemental NPRM specifies that 

replacing the existing FADEC 

assemblies with new or modified 

FADEC assemblies that include software 

version 7.6 is acceptable for compliance 

with paragraph (f) of the supplemental 

NPRM.) The commenter notes that, 

because the same features relating to 

temperature reading in FADEC software 

version 7.6 are included in software 

version 8.0, FADEC software version 8.0 

should also be referenced as an 

acceptable means of compliance with 

the proposed requirements. The 

commenter also lists the service 

bulletins for installing FADEC software 

version 8.0. 

We agree with the commenter’s 

request. EMBRAER has issued the 

service bulletins specified in the table 

below. 

Service Information for Installing 

FADEC Assemblies Having Software 

Version 8.0 

For EMBRAER Model— EMBRAER Service 

Bulletin Revision Date 

Which refers to 

Rolls-Royce Service 

Bulletin—

EMB–135ER, –135KE, –135KL, –135LR, –145, –145ER, 

–145MR, –145LR, –145XR, –145MP, –145EP.

145–73–0027 ......... Original ..... March 15, 2005 ...... AE3007A–73–079. 

EMB–135ER, –135KE, –135KL, –135LR, –145, –145ER, 

–145MR, –145LR, –145XR, –145MP, –145EP.

145–73–0028 ......... Original ..... March 15, 2005 ...... AE3007A–73–078. 

EMB–135ER, –135KE, –135KL, –135LR, –145, –145ER, 

–145MR, –145LR, –145XR, –145MP, –145EP.

145–73–0029 ......... Original ..... May 4, 2005 ........... AE3007A–73–075. 

EMB–135ER, –135KE, –135KL, –135LR, –145, –145ER, 

–145MR, –145LR, –145XR, –145MP, –145EP.

145–73–0029 ......... 01 ............. June 27, 2005 ........ AE3007A–73–075. 

EMB–135ER, –135KE, –135KL, –135LR, –145, –145ER, 

–145MR, –145LR, –145XR, –145MP, –145EP.

145–73–0030 ......... Original ..... May 5, 2005 ........... AE3007A–73–076. 

EMB–135ER, –135KE, –135KL, –135LR, –145, –145ER, 

–145MR, –145LR, –145XR, –145MP, –145EP.

145–73–0031 ......... Original ..... May 5, 2005 ........... AE3007A–73–077. 

EMB–135BJ ................................................................................. 145LEG–73–0005 .. Original ..... June 7, 2005 .......... AE3007A–73–079. 

EMB–135BJ ................................................................................. 145LEG–73–0006 .. Original ..... March 8, 2005 ........ AE3007A–73–078. 

These service bulletins describe 

procedures for replacing existing 

FADEC assemblies with FADEC 

assemblies that have software version 

8.0, including verifying the part number 

of the ITT trim plug and replacing it 

with an ITT trim plug of another part 

number if necessary. These service 

bulletins also refer to the Rolls-Royce 

service bulletins listed in the table 

above as additional sources of service 

information for replacing the FADEC 

assemblies. The EMBRAER service 

bulletins listed in the table also specify 

that installing the new or modified 

Federal Register / Vol. 70, No. 206 / Wednesday, October 26, 2005 / Rules and Regulations 61731 

FADEC assemblies that have FADEC 

software version 8.0 also necessitates 

upgrading the engine indication and 

crew alerting system (EICAS), central 

maintenance computer (CMC), and IC–

600 configuration modules, as 

applicable. 

We have revised paragraph (h) and 

Table 2 of this AD to include references 

to these service bulletins and the 

applicable actions in them. 

Request To Add Reference to RollsRoyce Service Bulletins 

One commenter requests that we 

revise Table 2 of the supplemental 

NPRM to give credit for replacing the 

FADEC assemblies with new or 

modified FADEC assemblies that 

include software version 7.6 in 

accordance with Rolls-Royce Service 

Bulletin AE3007A–73–067 or 

AE3007A–73–069, as applicable. The 

commenter states that adding these 

service bulletins to Table 2 would save 

it a lot of time that would otherwise be 

needed to request an Alternative 

Method of Compliance (AMOC) and 

would save the FAA time that would be 

needed to address those AMOCs. 

We do not agree that any change to 

this AD is necessary to meet the intent 

of the commenter’s request. Table 2 of 

this AD gives credit for replacing 

FADEC assemblies with new or 

modified FADEC assemblies that 

include software version 7.6 in 

accordance with, among other service 

bulletins, EMBRAER Service Bulletin 

145–73–0022 or 145–73–0024, both 

Revision 01, both dated July 15, 2004. 

We explain in the preamble of the 

supplemental NPRM that these 

EMBRAER Service Bulletins refer to 

Rolls-Royce Service Bulletin AE3007A–

73–067 and AE3007A–73–069, 

respectively, as additional sources of 

service information for replacing the 

FADEC assemblies. We find that doing 

the actions specified in Rolls-Royce 

Service Bulletin AE3007A–73–067 or 

AE3007A–73–069 is acceptable for 

compliance with the corresponding 

actions required by paragraph (h) of this 

AD, provided that all applicable EICAS, 

CMC, and IC–600 upgrades; as well as 

any other applicable actions associated 

with upgrading the EICAS, CMC, or IC–

600; are also done, as specified in 

paragraph 1.C., ‘‘Description—Time for 

Accomplishment,’’ of EMBRAER 

Service Bulletin 145–73–0022 or 145–

73–0024, both Revision 01, as required 

by paragraph (h) of this AD. No change 

to the AD is needed in this regard. 

Clarification of AMOC Paragraph 

We have revised this action to clarify 

the appropriate procedure for notifying 

the principal inspector before using any 

approved AMOC on any airplane to 

which the AMOC applies. 

Conclusion 

We have carefully reviewed the 

available data, including the comments 

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. 

Costs of Compliance 

The following table provides the 

estimated costs for U.S. operators to 

comply with this AD. 

ESTIMATED COSTS

Action Work hours 

Average 

labor rate 

per hour 

Parts Cost per 

airplane 

Number 

of U.S.- 

registered 

airplanes 

Fleet cost 

Modify the TAT sensor heating system .................... 8 $65 $443 $963 434 Up to $417,942. 

For airplanes modified in accordance 

with Revisions 04 through 08 of 

EMBRAER Service Bulletin 145–30–

0028, it will take about 1 work hour per 

airplane to do the additional 

modification specified in Part III of the 

Accomplishment Instructions of the 

service bulletin, at an average labor rate 

of $65 per work hour. Based on these 

figures, the estimated cost of doing this 

required action is $65 per airplane. 

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 

61732 Federal Register / Vol. 70, No. 206 / Wednesday, October 26, 2005 / Rules and Regulations 

by adding the following new 

airworthiness directive (AD): 

2005–22–08 Empresa Brasileira de 

Aeronautica S.A. (EMBRAER): 

Amendment 39–14352. Docket No. 

FAA–2004–18564; Directorate Identifier 

2004–NM–16–AD. 

Effective Date 

(a) This AD becomes effective November 

30, 2005. 

Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to EMBRAER Model 

EMB–135BJ, –135ER, –135KE, –135KL, 

–135LR, –145, –145ER, –145MR, –145LR, 

–145XR, –145MP, and –145EP airplanes; as 

identified in EMBRAER Service Bulletin 

145–30–0028, Revision 10, dated March 22, 

2005; certificated in any category. 

Unsafe Condition 

(d) This AD was prompted by a report 

indicating that the fully automated digital 

electronic control (FADEC) unit failed to 

compensate for ice accretion on the engine 

fan blades due to a false temperature signal 

from the total air temperature (TAT) sensor 

to the FADEC. We are issuing this AD to 

prevent failure of the TAT sensor, which 

could result in insufficient thrust to take off 

or (if coupled with the loss of an engine 

during takeoff) to abort the takeoff in a safe 

manner, and consequent reduced 

controllability of the airplane. 

Compliance 

(e) You are responsible for having the 

actions required by this AD performed within 

the compliance times specified, unless the 

actions have already been done. 

Modification 

(f) Within 180 days after the effective date 

of this AD: Modify the TAT sensor heating 

system in accordance with the 

Accomplishment Instructions of EMBRAER 

Service Bulletin 145–30–0028, Revision 10, 

dated March 22, 2005. 

Modifications Done According to Previous 

Revisions of the Service Bulletin 

(g) Actions done before the effective date 

of this AD are acceptable for compliance with 

the corresponding requirements of this AD as 

specified in paragraphs (g)(1) and (g)(2) of 

this AD. 

(1) Modifications in accordance with 

EMBRAER Service Bulletin 145–30–0028, 

Revision 09, dated March 1, 2004, are 

acceptable for compliance with paragraph (f) 

of this AD. 

(2) Modifications in accordance with the 

revisions of the service bulletin in Table 1 of 

this AD are acceptable for compliance with 

the corresponding action in this AD, 

provided that the additional actions specified 

in PART III of the Accomplishment 

Instructions of EMBRAER Service Bulletin 

145–30–0028, Revision 09, dated March 1, 

2004, or Revision 10, dated March 22, 2005, 

are accomplished within the compliance 

time required by paragraph (f) of this AD. 

TABLE 1.—PREVIOUS REVISIONS OF THE SERVICE BULLETIN

EMBRAER Service Bulletin Revision Date 

145–30–0028 ......................................................................................................................................................... 04 March 13, 2001. 

145–30–0028 ......................................................................................................................................................... 05 May 24, 2001. 

145–30–0028 ......................................................................................................................................................... 06 September 26, 2001. 

145–30–0028 ......................................................................................................................................................... 07 April 10, 2003. 

145–30–0028 ......................................................................................................................................................... 08 August 20, 2003. 

Credit for Replacement of FADEC 

Assemblies 

(h) Replacing the existing FADEC 

assemblies with new or modified FADEC 

assemblies that include software version 7.6 

or 8.0, in accordance with the 

Accomplishment Instructions of the 

applicable service bulletin listed in Table 2 

of this AD, is acceptable for compliance with 

paragraph (f) of this AD. If the FADEC 

assemblies are replaced with new or 

modified assemblies as specified in this 

paragraph, all applicable engine indication 

and crew alerting system (EICAS), central 

maintenance computer (CMC), and IC–600 

upgrades; as well as any other applicable 

actions associated with upgrading the EICAS, 

CMC, or IC–600; must also be done, as 

specified in the section of the service bulletin 

identified in the ‘‘Paragraph Where Upgrades 

are Identified’’ column of Table 2 of this AD. 

TABLE 2.—SERVICE BULLETINS FOR UPGRADING FADEC ASSEMBLIES

For EMBRAER Model— EMBRAER Service 

Bulletin Revision Date Paragraph where upgrades are identified 

EMB–135ER, –135KE, –135KL, –135LR, –145, 

–145ER, –145MR, –145LR, –145XR, –145MP, 

–145EP.

145–73–0021 ......... Original ..... July 23, 2004 ......... 1.C., ‘‘Description—Time 

for Accomplishment’’. 

EMB–135ER, –135KE, –135KL, –135LR, –145, 

–145ER, –145MR, –145LR, –145XR, –145MP, 

–145EP.

145–73–0022 ......... 01 ............. July 15, 2004 ......... 1.C., ‘‘Description—Time 

for Accomplishment’’. 

EMB–135ER, –135KE, –135KL, –135LR, –145, 

–145ER, –145MR, –145LR, –145XR, –145MP, 

–145EP.

145–73–0023 ......... Original ..... June 28, 2004 ........ 1.C., ‘‘Description—Time 

for Accomplishment’’. 

EMB–135ER, –135KE, –135KL, –135LR, –145, 

–145ER, –145MR, –145LR, –145XR, –145MP, 

–145EP.

145–73–0024 ......... 01 ............. July 15, 2004 ......... 1.C., Description—Time for 

Accomplishment’’. 

EMB–135ER, –135KE, –135KL, –135LR, –145, 

–145ER, –145MR, –145LR, –145XR, –145MP, 

–145EP.

145–73–0025 ......... Original ..... July 23, 2004 ......... 1.C., ‘‘Description—Time 

for Accomplishment’’. 

EMB–135ER, –135KE, –135KL, –135LR, –145, 

–145ER, –145MR, –145LR, –145XR, –145MP, 

–145EP.

145–73–0027 ......... Original ..... March 15, 2005 ...... 1.B., ‘‘Concurrent Requirements’’. 

EMB–135ER, –135KE, –135KL, –135LR, –145, 

–145ER, –145MR, –145LR, –145XR, –145MP, 

–145EP.

145–73–0028 ......... Original ..... March 15, 2005 ...... 1.B., ‘‘Concurrent Requirements’’. 

EMB–135ER, –135KE, –135KL, –135LR, –145, 

–145ER, –145MR, –145LR, –145XR, –145MP, 

–145EP.

145–73–0029 ......... Original ..... May 4, 2005 ........... 1.B., ‘‘Concurrent Requirements’’. 

Federal Register / Vol. 70, No. 206 / Wednesday, October 26, 2005 / Rules and Regulations 61733 

TABLE 2.—SERVICE BULLETINS FOR UPGRADING FADEC ASSEMBLIES—Continued 

For EMBRAER Model— EMBRAER Service 

Bulletin Revision Date Paragraph where upgrades are identified 

EMB–135ER, –135KE, –135KL, –135LR, –145, 

–145ER, –145MR, –145LR, –145XR, –145MP, 

–145EP.

145–73–0029 ......... 01 ............. June 27, 2005 ........ 1.B., ‘‘Concurrent Requirements’’. 

EMB–135ER, –135KE, –135KL, –135LR, –145, 

–145ER, –145MR, –145LR, –145XR, –145MP, 

–145EP.

145–73–0030 ......... Original ..... May 5, 2005 ........... 1.B., ‘‘Concurrent Requirements’’. 

EMB–135ER, –135KE, –135KL, –135LR, –145, 

–145ER, –145MR, –145LR, –145XR, –145MP, 

–145EP.

145–73–0031 ......... Original ..... May 5, 2005 ........... 1.B., ‘‘Concurrent Requirements’’. 

EMB–135BJ .................................................................... 145LEG–73–0003 .. 01 ............. July 15, 2004 ......... 1.C., ‘‘Description—Time 

for Accomplishment’’. 

EMB–135BJ .................................................................... 145LEG–73–0004 .. 02 ............. October 6, 2004 ..... 1.C., ‘‘Description—Time 

for Accomplishment’’. 

EMB–135BJ .................................................................... 145LEG–73–0005 .. Original ..... June 7, 2005 .......... 1.D., ‘‘Description’’. 

EMB–135BJ .................................................................... 145LEG–73–0006 .. Original ..... March 8, 2005 ........ 1.B., ‘‘Concurrent Requirements’’. 

EMB–145XR .................................................................... 145–73–0026 ......... Original ..... June 28, 2004 ........ 1.C., ‘‘Description—Time 

for Accomplishment’’. 

Alternative Methods of Compliance 

(AMOCs) 

(i)(1) The Manager, International Branch, 

ANM–116, Transport Airplane Directorate, 

FAA, has the authority to approve AMOCs 

for this AD, if requested in accordance with 

the procedures found in 14 CFR 39.19. 

(2) Before using any AMOC approved in 

accordance with 14 CFR 39.19 on any 

airplane to which the AMOC applies, notify 

the appropriate principal inspector in the 

FAA Flight Standards Certificate Holding 

District Office. 

Related Information 

(j) Brazilian airworthiness directive 2004–

01–02R2, dated November 29, 2004, also 

addresses the subject of this AD. 

Material Incorporated by Reference 

(k) You must use EMBRAER Service 

Bulletin 145–30–0028, Revision 10, dated 

March 22, 2005, to perform the actions that 

are required by this AD, unless the AD 

specifies otherwise. The Director of the 

Federal Register approved the incorporation 

by reference of this document in accordance 

with 5 U.S.C. 552(a) and 1 CFR part 51. 

Contact Empresa Brasileira de Aeronautica 

S.A. (EMBRAER), P.O. Box 343—CEP 12.225, 

Sao Jose dos Campos—SP, Brazil, for a copy 

of this service information. You may review 

copies at the Docket Management Facility, 

U.S. Department of Transportation, 400 

Seventh Street SW., room PL–401, Nassif 

Building, Washington, DC; on the Internet at 

http://dms.dot.gov; or at the National 

Archives and Records Administration 

(NARA). For information on the availability 

of this material at the 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 October 

18, 2005. 

Kevin M. Mullin, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 05–21310 Filed 10–25–05; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 71 

[Docket No. FAA–2005–20699; Airspace 

Docket No. 04–ASO–19] 

RIN 2120–AA66 

Establishment of Area Navigation 

Instrument Flight Rules Terminal 

Transition Routes (RITTR); Cincinnati, 

OH 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: This action establishes three 

Area Navigation Instrument Flight Rules 

Terminal Transition Routes (RITTR) in 

the Cincinnati, OH, terminal area. The 

FAA originally proposed to establish 

four routes as part of this action, but one 

route (T–212) was deleted because it did 

not meet RITTR design criteria and its 

short length would provide limited 

benefits. RITTR’s are low altitude Air 

Traffic Service (ATS) routes, based on 

Area Navigation (RNAV), for use by 

aircraft having Instrument Flight Rules 

(IFR)-approved Global Positioning 

System (GPS)/Global Navigation 

Satellite System (GNSS) equipment. The 

FAA is taking this action to enhance 

safety and facilitate the more flexible 

and efficient use of the navigable 

airspace in the Cincinnati terminal area. 

EFFECTIVE DATE: 0901 UTC, December 

22, 2005. 

FOR FURTHER INFORMATION CONTACT: Paul 

Gallant, Airspace and Rules, Office of 

System Operations Airspace and AIM, 

Federal Aviation Administration, 800 

Independence Avenue, SW., 

Washington, DC 20591; telephone: (202) 

267–8783. 

SUPPLEMENTARY INFORMATION: 

History 

On July 6, 2005, the FAA published 

in the Federal Register a notice of 

proposed rulemaking to establish four 

RITTR’s in the Cincinnati, OH, terminal 

area (70 FR 38826). Interested parties 

were invited to participate in this 

rulemaking effort by submitting written 

comments on this proposal to the FAA. 

Two comments were received in 

response to the NPRM. 

Analysis of Comments 

The Aircraft Owners and Pilots 

Association wrote in support of the 

proposal. The second commenter 

expressed general support for the 

concept of terminal transition routes to 

assist IFR traffic transitioning Class B 

airspace, but stated that the proposed 

Cincinnati RITTRs do not accomplish 

this, and that IFR traffic (usually general 

aviation flights) would continue to be 

forced to make long detours around the 

Class B airspace. The commenter 

recommended that the FAA design 

transition routes that extend diagonally 

(northwest to southeast and southwest 

to northeast) across the Cincinnati/ 

Northern Kentucky International 

Airport (CVG) Class B airspace area. The 

FAA responds that these RITTRs are