8622 Federal Register / Vol. 72, No. 38 / Tuesday, February 27, 2007 / Rules and Regulations 

attachment bolts. We are issuing this AD to 

detect and correct missing or fractured 

attachment bolts, which could lead to the 

loss of an engine exhaust nozzle during flight 

and consequent structural damage to the 

airplane and hazard to people or property on 

the ground. Damage to the airplane could 

cause the airplane to yaw and result in 

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. 

Repetitive Inspections 

(f) Within 1,500 flight hours after the 

effective date of this AD: For the left and 

right engine exhaust nozzles, do a detailed 

inspection of the bolts that attach the exhaust 

nozzle to the aft engine flange to determine 

if any bolts are missing or fractured, in 

accordance with Part A of the 

Accomplishment Instructions of Bombardier 

Service Bulletin 601R–78–021, dated June 2, 

2006. If no bolt of an engine exhaust nozzle 

is missing or fractured, repeat the detailed 

inspection for that engine exhaust nozzle 

thereafter at intervals not to exceed 1,500 

flight hours, until the replacement specified 

in paragraph (g) or (h) of this AD is 

accomplished. 

Note 1: For the purposes of this AD, a 

detailed inspection is: ‘‘An intensive 

examination of a specific item, installation, 

or assembly to detect damage, failure, or 

irregularity. Available lighting is normally 

supplemented with a direct source of good 

lighting at an intensity deemed appropriate. 

Inspection aids such as mirror, magnifying 

lenses, etc., may be necessary. Surface 

cleaning and elaborate procedures may be 

required.’’

Corrective Action, if Necessary 

(g) If any bolt of an engine exhaust nozzle 

is found missing or fractured during any 

inspection required by paragraph (f) of this 

AD, before further flight, replace the existing 

bolts that attach the exhaust nozzle to the aft 

engine flange with new, improved bolts, in 

accordance with Part B of the 

Accomplishment Instructions of Bombardier 

Service Bulletin 601R–78–021, dated June 2, 

2006. Accomplishing the bolt replacement 

for an engine exhaust nozzle terminates the 

repetitive inspections required by paragraph 

(f) of this AD for that engine exhaust nozzle 

only. 

Note 2: Bombardier Service Bulletin 601R–

78–021, dated June 2, 2006, refers to 

Bombardier Service Bulletin CF34-NAC–78–

024, Revision 4, dated November 10, 2005, as 

an additional source of service information 

for accomplishment of the replacement. 

Terminating Action 

(h) Within 4,000 flight hours after the 

effective date of this AD: For the left and 

right engine exhaust nozzles, replace the 

existing bolts that attach the exhaust nozzle 

to the aft engine flange with new, improved 

bolts, in accordance with Part B of the 

Accomplishment Instructions of Bombardier 

Service Bulletin 601R–78–021, dated June 2, 

2006. Accomplishing the replacement for the 

left and right engine exhaust nozzles 

terminates all of the inspections required by 

paragraph (f) of this AD. 

Alternative Methods of Compliance 

(AMOCs) 

(i)(1) The Manager, New York Aircraft 

Certification Office, 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 § 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) Canadian airworthiness directive CF–

2006–19, dated July 28, 2006, also addresses 

the subject of this AD. 

Material Incorporated by Reference 

(k) You must use Bombardier Service 

Bulletin 601R–78–021, dated June 2, 2006, 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 Bombardier, Inc., Canadair, 

Aerospace Group, P.O. Box 6087, Station 

Centre-ville, Montreal, Quebec H3C 3G9, 

Canada, for a copy of this service 

information. You may review copies at the 

FAA, Transport Airplane Directorate, 1601 

Lind Avenue, S.W., 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 February 

13, 2007. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. E7–2973 Filed 2–26–07; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2006–26462; Directorate 

Identifier 2006–NM–221–AD; Amendment 

39–14952; AD 2007–04–20] 

RIN 2120–AA64 

Airworthiness Directives; Empresa 

Brasileira de Aeronautica S.A. 

(EMBRAER) Model ERJ 170–100 LR, 

–100 STD, –100 SE, –100 SU, –200 LR, 

–200 STD, and –200 SU Airplanes and 

Model ERJ 190 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 Model ERJ 170–100 LR, –100 

STD, –100 SE, –100 SU, –200 LR, –200 

STD, and –200 SU airplanes and Model 

ERJ 190 airplanes. This AD requires 

inspecting to determine the part number 

and serial number of the deployment 

actuator of the ram air turbine (RAT) 

and related investigative and corrective 

actions if necessary. This AD results 

from reports that the RAT may not fully 

deploy due to galling between the 

piston rod and gland housing of the 

RAT deployment actuator. We are 

issuing this AD to prevent the RAT from 

failing to deploy, which could result in 

loss of control of the airplane during inflight emergencies. 

DATES: This AD becomes effective April 

3, 2007. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in the AD 

as of April 3, 2007. 

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, 

Transport Airplane Directorate, FAA, 

1601 Lind Avenue, SW., Renton, 

Washington 98057–3356; telephone 

(425) 227–1175; fax (425) 227–1149. 

SUPPLEMENTARY INFORMATION: 


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Federal Register / Vol. 72, No. 38 / Tuesday, February 27, 2007 / Rules and Regulations 8623 

Examining the Docket 

You may examine the airworthiness 

directive (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 notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to include an AD that would 

apply to certain EMBRAER Model ERJ 

170–100 LR, –100 STD, –100 SE, –100 

SU, –200 LR, –200 STD, and –200 SU 

airplanes and Model ERJ 190 airplanes. 

That NPRM was published in the 

Federal Register on December 8, 2006 

(71 FR 71096). That NPRM proposed to 

require inspecting to determine the part 

number and serial number of the 

deployment actuator of the ram air 

turbine (RAT) and related investigative 

and corrective actions if necessary. 

Comments 

We provided the public the 

opportunity to participate in the 

development of this AD. We received no 

comments on the NPRM or on the 

determination of the cost to the public. 

Clarification of Service Bulletin 

Reference Paragraph 

We have added to paragraph (f)(1) of 

this AD three airplane models that were 

unintentionally left out of that 

paragraph. 

Conclusion 

We have carefully reviewed the 

available data and determined that air 

safety and the public interest require 

adopting the AD with the change 

described previously. We have 

determined that this change 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, at an average 

labor rate of $80 per hour. 

ESTIMATED COSTS

Action Work hours Cost per 

airplane 

Number of U.S.- 

registered 

airplanes 

Fleet cost 

Inspection to determine part and serial numbers 1 $80 ................................ 76 .................................. $6,080.

Inspection of piston rod ......................................... 1 $80, per inspection 

cycle.

Up to 76 ........................ Up to $6,080, per inspection cycle. 

Replacement of RAT deployment actuator ........... 4 $320 .............................. Up to 76 ........................ Up to $24,320. 

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 adding the following new 

airworthiness directive (AD): 

2007–04–20 Empresa Brasileira de 

Aeronautica S.A. (EMBRAER): 

Amendment 39–14952. Docket No. 

FAA–2006–26462; Directorate Identifier 

2006–NM–221–AD. 

Effective Date 

(a) This AD becomes effective April 3, 

2007. 

Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to EMBRAER Model 

ERJ 170–100 LR, –100 STD, –100 SE, –100 

SU, –200 LR, –200 STD, and –200 SU 

airplanes, as identified in EMBRAER Service 

Bulletin 170–24–0026, dated December 22, 

2005; and Model ERJ 190–100 STD, –100 LR, 

and –100 IGW airplanes, as identified in 

EMBRAER Service Bulletin 190–24–0003, 

dated December 22, 2005; certificated in any 

category. 

Unsafe Condition 

(d) This AD results from reports that the 

ram air turbine (RAT) may not fully deploy 

due to galling between the piston rod and 

gland housing of the RAT deployment 

actuator. We are issuing this AD to prevent 

the RAT from failing to deploy, which could 

result in loss of control of the airplane during 

in-flight emergencies. 


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8624 Federal Register / Vol. 72, No. 38 / Tuesday, February 27, 2007 / Rules and Regulations 

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. 

Service Bulletin Reference 

(f) The term ‘‘service bulletin,’’ as used in 

this AD, means the Accomplishment 

Instructions of the service bulletins identified 

in paragraphs (f)(1) and (f)(2) of this AD. 

Where these service bulletins specify 

returning affected parts to Hamilton 

Sundstrand, this AD does not require that 

action. 

(1) For Model ERJ 170–100 LR, –100 STD, 

–100 SE, –100 SU, –200 LR, –200 STD, and 

–200 SU airplanes: EMBRAER Service 

Bulletin 170–24–0026, dated December 22, 

2005. 

(2) For Model ERJ 190–100 STD, –100 LR, 

and –100 IGW airplanes: EMBRAER Service 

Bulletin 190–24–0003, dated December 22, 

2005. 

Note 1: The EMBRAER service bulletins 

refer to Hamilton Sundstrand Service 

Bulletin ERPS37A–24–1, dated December 6, 

2005, as an additional source of service 

information for inspecting for galling of the 

piston rod of the RAT deployment actuator 

and re-identifying the actuator. The Hamilton 

Sundstrand service bulletin is included as 

Appendix 1 of the EMBRAER service 

bulletins. 

Inspection To Determine Part Number (P/N) 

and Serial Number (S/N) 

(g) Within 600 flight hours or 3 months 

after the effective date of this AD, whichever 

occurs first: Inspect to determine the part 

number and serial number of the RAT 

deployment actuator, in accordance with the 

applicable service bulletin. A review of 

airplane maintenance records is acceptable in 

lieu of this inspection if the part number and 

serial number of the RAT deployment 

actuator can be conclusively determined 

from that review. 

(1) If the part number of the actuator is not 

P/N 1703785: No further action is required by 

this AD, except as provided by paragraph (i) 

of this AD. 

(2) If the part number of the actuator is 

P/N 1703785 and the serial number is S/N 

0004, 0005, or 0101 through 0190 inclusive, 

or the part number or serial number cannot 

be conclusively determined: Within 600 

flight hours or 3 months after the effective 

date of this AD, whichever occurs first, 

deploy the RAT, and do the actions specified 

in paragraph (g)(2)(i) or (g)(2)(ii) of this AD, 

as applicable, in accordance with the 

applicable service bulletin. 

(i) If the RAT does not fully deploy or if 

it deploys with hesitation: Before further 

flight, replace the RAT deployment actuator 

with a modified and reidentified or new, 

improved actuator, having P/N 1703785A. 

(ii) If the RAT fully deploys without 

hesitation: Before further flight, perform a 

general visual inspection for galling of the 

piston rod of the RAT deployment actuator. 

If no evidence of galling is detected, repeat 

the inspection for galling at intervals not to 

exceed 1,200 flight hours or 5 months, 

whichever occurs first, and before further 

flight after each deployment of the RAT. If 

any evidence of galling is found, before 

further flight, replace the RAT deployment 

actuator with a modified and reidentified or 

new, improved RAT deployment actuator 

having P/N 1703785A. Replacing the RAT 

deployment actuator terminates the repetitive 

inspections required by this paragraph for 

that RAT deployment actuator only. 

Note 2: For the purposes of this AD, a 

general visual inspection is: ‘‘A visual 

examination of an interior or exterior area, 

installation, or assembly to detect obvious 

damage, failure, or irregularity. This level of 

inspection is made from within touching 

distance unless otherwise specified. A mirror 

may be necessary to ensure visual access to 

all surfaces in the inspection area. This level 

of inspection is made under normally 

available lighting conditions such as 

daylight, hangar lighting, flashlight, or 

droplight and may require removal or 

opening of access panels or doors. Stands, 

ladders, or platforms may be required to gain 

proximity to the area being checked.’’

(3) If the part number of the RAT 

deployment actuator is P/N 1703785, and the 

serial number is S/N 0191 through 0242 

inclusive: Within 3,000 flight hours or 12 

months after the effective date of this AD, 

whichever occurs first, reidentify the RAT 

deployment actuator with new P/N 

1703785A in accordance with the applicable 

service bulletin. 

Terminating Action for Repetitive 

Inspections 

(h) Within 3,000 flight hours or 12 months 

after the effective date of this AD, whichever 

occurs first: Replace all RAT deployment 

actuators having P/N 1703785 and having 

S/N 0004, 0005, or 0101 through 0190 

inclusive, with modified and reidentified or 

new, improved actuators having P/N 

1703785A, in accordance with the applicable 

service bulletin. Replacing all of the RAT 

deployment actuators terminates the 

repetitive inspections required by paragraph 

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

Parts Installation 

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

person may install a RAT deployment 

actuator having P/N 1703785 on any 

airplane. 

Alternative Methods of Compliance 

(AMOCs) 

(j)(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 § 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 

(k) Brazilian airworthiness directives 

2006–05–06, effective June 14, 2006, and 

2006–05–09, effective June 19, 2006, also 

address the subject of this AD. 

Material Incorporated by Reference 

(l) You must use EMBRAER Service 

Bulletin 170–24–0026, dated December 22, 

2005; or EMBRAER Service Bulletin 190–24–

0003, dated December 22, 2005; as 

applicable, 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 these documents 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 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/ibr-locations.html. 

Issued in Renton, Washington, on February 

12, 2007. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. E7–2976 Filed 2–26–07; 8:45 am] 

BILLING CODE 4910–13–P 

INTERNATIONAL TRADE 

COMMISSION 

19 CFR Part 208 

Investigations Relating to Commercial 

Availability Under the African Growth 

and Opportunity Act 

AGENCY: United States International 

Trade Commission. 

ACTION: Interim rule with request for 

comments. 

SUMMARY: The Commission is amending 

its rules of practice and procedure to 

add a new part 208 in order to 

implement section 112(c) of the African 

Growth and Opportunity Act (AGOA), 

as amended (19 U.S.C. 3721(c)). The 

provisions addressing the Commission’s 

role are contained in amendments to 

AGOA which the President signed into 

law on December 20, 2006. The interim 

rules provide for Commission 

investigations, determinations, and 

reports under section 112(c) of AGOA, 

and also specify the information that 

must be included in a properly filed 

petition. Interim rules are necessary 

because the new provisions became 

effective on the day of enactment; in the 

absence of interim rules, the 

Commission will have no procedures in 

place with respect to these proceedings. 

DATES: This interim rule is effective 

February 27, 2007. Comments 

concerning these interim rules should 


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