60802 Federal Register / Vol. 69, No. 197 / Wednesday, October 13, 2004 / Rules and Regulations 

2004–20–11 Airbus: Amendment 39–13816. 

Docket No. FAA–2004–18602; 

Directorate Identifier 2003–NM–160–AD. 

Effective Date 

(a) This airworthiness directive (AD) 

becomes effective November 17, 2004.

Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to all airplanes, 

certificated in any category, as identified in 

in Table 1 of this AD.

TABLE 1.—APPLICABILITY

Model Serial nos. 

A300 B2 and B4 series airplanes.All. 

A300 B4–600, B4–600R, 

and F4–600R series airplanes, and Model C4–

605R Variant F airplanes 

(collectively called A300–

600).

796 and earlier. 

Unsafe Condition 

(d) This AD was prompted by the results 

of an engineering evaluation that revealed 

that several repairs and some allowable 

damage limits specified in the structural 

repair manuals do not provide adequate 

static and/or fatigue strength for repaired 

wing slats. We are issuing this AD to find and 

fix previously done repairs of the wing slats 

that have inadequate static and/or fatigue 

strength, which, if not corrected, could result 

in loss of the slats 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. 

Service Bulletins 

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

this AD, means the Accomplishment 

Instructions of the applicable service bulletin 

listed in Table 2 of this AD.

TABLE 2.—SERVICE BULLETINS

For model Airbus service bulletin 

(1) A300 B4–600, B4–600R, and F4–600R series airplanes, and Model 

C4–605R Variant F airplanes (collectively called A300–600).

A300–57–6092, Revision 02, dated November 21, 2002. 

(2) A300 B2 and B4 series airplanes ....................................................... A300–57–0238, Revision 02, dated November 21, 2002. 

Inspection and Related Investigative/

Corrective Actions 

(g) Within 18 months or 1,500 flight cycles 

from the effective date of this AD, whichever 

occurs first: Do a detailed inspection of the 

skin panels of the wing slats for damage and 

certain repairs, and do all applicable related 

investigative/corrective actions, by 

accomplishing all the actions in the 

applicable service bulletin. Do the actions in 

accordance with the service bulletin, except 

as required by paragraphs (h) and (i) of this 

AD. Do any related investigative/corrective 

action before further flight.

Note 1: For the purposes of this AD, a 

detailed inspection is ‘‘an intensive visual 

examination of a specific structural area, 

system, installation, or assembly to detect 

damage, failure, or irregularity. Available 

lighting is normally supplemented with a 

direct source of good lighting at intensity 

deemed appropriate by the inspector. 

Inspection aids such as mirror, magnifying 

lenses, etc., may be used. Surface cleaning 

and elaborate access procedures may be 

required.’’

Repair 

(h) If any damage is detected during the 

inspection required by paragraph (g) of this 

AD, and the service bulletin recommends 

contacting Airbus for appropriate action: 

Before further flight, repair in accordance 

with a method approved by either the 

Manager, International Branch, ANM–116, 

FAA, Transport Airplane Directorate; or the 

Direction Ge ́ne ́rale de l’Aviation Civile 

(DGAC) (or its delegated agent). 

(i) If any repair that has a specific Airbus 

approval other than a Repair Approval Sheet 

signed by the DGAC (or its delegated agent) 

is found during the inspection required by 

paragraph (g) of this AD, and the service 

bulletin specifies that the related 

investigative action is not necessary: Before 

further flight, do the applicable related 

investigative/corrective actions required by 

paragraph (g) of this AD. 

(j) Where there are differences between this 

AD and the service bulletin, the AD prevails. 

Alternative Methods of Compliance 

(AMOCs) 

(k) The Manager, International Branch, 

ANM–116, has the authority to approve 

AMOCs for this AD, if requested using the 

procedures found in 14 CFR 39.19. 

Related Information 

(l) French airworthiness directive 2003–

086(B), effective March 15, 2003, also 

addresses the subject of this AD. 

Material Incorporated by Reference 

(m) You must use Airbus Service Bulletin 

A300–57–0238, Revision 02, dated November 

21, 2002; or Airbus Service Bulletin A300–

57–6092, Revision 02, dated November 21, 

2002; as applicable; unless the AD specifies 

otherwise. The Director of the Federal 

Register approves the incorporation by 

reference of these documents in accordance 

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

copies of the service information, contact 

Airbus, 1 Rond Point Maurice Bellonte, 

31707 Blagnac Cedex, France. For 

information on the availability of this 

material at the National Archives and 

Records Administration (NARA), call (202) 

741–6030, or go to http://www.archives.gov/

federal_register/code_of_federal_regulations/

ibr_locations.html. You may view the AD 

docket at the Docket Management Facility, 

U.S. Department of Transportation, 400 

Seventh Street SW., room PL–401, Nassif 

Building, Washington, DC.

Issued in Renton, Washington, on 

September 29, 2004. 

Kalene C. Yanamura, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service.

[FR Doc. 04–22469 Filed 10–12–04; 8:45 am] 

BILLING CODE 4910–13–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. 2003–NM–85–AD; Amendment 

39–13818; AD 2004–20–13] 

RIN 2120–AA64 

Airworthiness Directives; Empresa 

Brasileira de Aeronautica S.A. 

(EMBRAER) Model EMB–135 and 

EMB–145 Series Airplanes

AGENCY: Federal Aviation 

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment adopts a 

new airworthiness directive (AD), 

applicable to certain EMBRAER Model 

EMB–135 and EMB–145 series 

airplanes, that requires inspection of the 

housings of the main landing gear 

(MLG) leg strut bushings, and related 

investigative and corrective actions, and 

other specified actions. The actions 

specified by this AD are intended to 

prevent corrosion of the housings of the 

MLG leg strut bushings and consequent 

failure of the MLG. This action is 

Federal Register / Vol. 69, No. 197 / Wednesday, October 13, 2004 / Rules and Regulations 60803

intended to address the identified 

unsafe condition.

DATES: Effective November 17, 2004. 

The incorporation by reference of a 

certain publication listed in the 

regulations is approved by the Director 

of the Federal Register as of November 

17, 2004.

ADDRESSES: The service information 

referenced in this AD may be obtained 

from Empresa Brasileira de Aeronautica 

S.A. (EMBRAER), P.O. Box 343—CEP 

12.225, Sao Jose dos Campos—SP, 

Brazil. This information may be 

examined at the Federal Aviation 

Administration (FAA), Transport 

Airplane Directorate, Rules Docket, 

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/

code_of_federal_regulations/

ibr_locations.html.

FOR FURTHER INFORMATION CONTACT: Dan 

Rodina, Aerospace Engineer; 

International Branch, ANM–116, FAA, 

Transport Airplane Directorate, 1601 

Lind Avenue, SW., Renton, Washington 

98055–4056; telephone (425) 227–2125; 

fax (425) 227–1149.

SUPPLEMENTARY INFORMATION: A 

proposal to amend part 39 of the Federal 

Aviation Regulations (14 CFR part 39) to 

include an airworthiness directive (AD) 

that is applicable to certain EMBRAER 

Model EMB–135 and EMB–145 series 

airplanes was published as a 

supplemental notice of proposed 

rulemaking (NPRM) in the Federal 

Register on July 22, 2004 (69 FR 43777). 

That action proposed to require 

inspection of the housings of the main 

landing gear (MLG) leg strut bushings, 

related investigative and corrective 

actions, and other specified actions. 

Comments 

Interested persons have been afforded 

an opportunity to participate in the 

making of this amendment. No 

comments were submitted in response 

to the proposal or the FAA’s 

determination of the cost to the public. 

Conclusion 

The FAA has determined that air 

safety and the public interest require the 

adoption of the rule as proposed. 

Cost Impact 

We estimate that 75 airplanes of U.S. 

registry will be affected by this 

proposed AD. 

It will take approximately 14 work 

hours per airplane to accomplish the 

inspection of the bushing housings for 

corrosion, at an average labor rate of $65 

per work hour. Based on these figures, 

the cost impact of the inspection on U.S. 

operators is estimated to be $68,250, or 

$910 per airplane. 

The cost impact figure discussed 

above is based on assumptions that no 

operator has yet accomplished any of 

the requirements of this AD action, and 

that no operator would accomplish 

those actions in the future if this AD 

were not adopted. The cost impact 

figures discussed in AD rulemaking 

actions represent only the time 

necessary to perform the specific actions 

actually required by the AD. These 

figures typically do not include 

incidental costs, such as the time 

required to gain access and close up, 

planning time, or time necessitated by 

other administrative actions. 

Regulatory Impact 

The regulations adopted herein 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. Therefore, it is 

determined that this final rule does not 

have federalism implications under 

Executive Order 13132. 

For the reasons discussed above, I 

certify that this action (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. A final evaluation has 

been prepared for this action and it is 

contained in the Rules Docket. A copy 

of it may be obtained from the Rules 

Docket at the location provided under 

the caption ADDRESSES.

List of Subjects in 14 CFR Part 39 

Air transportation, Aircraft, Aviation 

safety, Incorporation by reference, 

Safety.

Adoption of the Amendment

■ Accordingly, pursuant to the authority 

delegated to me by the Administrator, 

the Federal Aviation Administration 

amends part 39 of the Federal Aviation 

Regulations (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. Section 39.13 is amended by adding 

the following new airworthiness 

directive:

2004–20–13 Empresa Brasileira de 

Aeronautica S.A. (EMBRAER):

Amendment 39–13818. Docket 2003–

NM–85–AD.

Applicability: Model EMB–135 and EMB–

145 series airplanes, certificated in any 

category, equipped with a main landing gear 

(MLG) leg strut having a part number (P/N) 

and serial number (S/N) listed in the table 

under the heading ‘‘Affected component’’ in 

paragraph 1.B., ‘‘Effectivity,’’ of EMBRAER 

Service Bulletin 145–32–0066, Change 03, 

dated April 19, 2004. 

Compliance: Required as indicated, unless 

accomplished previously. 

To prevent corrosion of the housings of the 

main landing gear (MLG) leg strut bushings 

and consequent failure of the MLG, 

accomplish the following: 

Inspection and Investigative and Corrective 

Actions 

(a) Within 5,500 flight hours after the 

effective date of this AD, perform a detailed 

inspection of the housings of the MLG leg 

strut bushings for corrosion per the 

Accomplishment Instructions of EMBRAER 

Service Bulletin 145–32–0066, Change 03, 

dated April 19, 2004. 

(1) If no corrosion is found, before further 

flight, do all applicable actions in and per the 

Accomplishment Instructions of the service 

bulletin. 

(2) If any corrosion is found, before further 

flight, do all applicable investigative and 

corrective actions in and per the 

Accomplishment Instructions of the service 

bulletin.

Note 1: For the purposes of this AD, a 

detailed inspection is defined as: ‘‘An 

intensive visual examination of a specific 

structural area, system, installation, or 

assembly to detect damage, failure, or 

irregularity. Available lighting is normally 

supplemented with a direct source of good 

lighting at intensity deemed appropriate by 

the inspector. Inspection aids such as mirror, 

magnifying lenses, etc., may be used. Surface 

cleaning and elaborate access procedures 

may be required.’’

Note 2: EMBRAER Service Bulletin 145–

32–0066, Change 03, dated April 19, 2004, 

refers to Embraer Liebherr Equipamentos do 

Brasil S.A. (ELEB) Service Bulletin 2309–

2006–32–01, Revision 03, dated April 19, 

2004, as an additional source of service 

information for the inspection and repair of 

the MLG leg strut bushings. The ELEB service 

bulletin is included within the EMBRAER 

service bulletin.

Inspections Accomplished per Previous 

Issue of Service Bulletin 

(b) Inspections and related investigative 

and corrective actions, accomplished before 

the effective date of this AD per EMBRAER 

Service Bulletin 145–32–0066, dated January 

8, 2002; Change 01, dated August 15, 2002; 

60804 Federal Register / Vol. 69, No. 197 / Wednesday, October 13, 2004 / Rules and Regulations 

or Change 02, dated February 26, 2004; are 

considered acceptable for compliance with 

the corresponding action specified in this 

AD. 

Alternative Methods of Compliance 

(c) In accordance with 14 CFR 39.19, the 

Manager, International Branch, ANM–116, 

Transport Airplane Directorate, FAA, is 

authorized to approve alternative methods of 

compliance for this AD. 

Incorporation by Reference 

(d) Unless otherwise specified in this AD, 

the actions must be done in accordance with 

EMBRAER Service Bulletin 145–32–0066, 

Change 03, dated April 19, 2004. This 

incorporation by reference was approved by 

the Director of the Federal Register in 

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

part 51. Copies may be obtained from 

Empresa Brasileira de Aeronautica S.A. 

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

Jose dos Campos—SP, Brazil. Copies may be 

inspected 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/

code_of_federal_regulations/

ibr_locations.html.

Note 3: The subject of this AD is addressed 

in Brazilian airworthiness directive 2002–12–

01, effective January 6, 2003. 

Effective Date 

(e) This amendment becomes effective on 

November 17, 2004.

Issued in Renton, Washington, on 

September 30, 2004. 

Kevin M. Mullin, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service.

[FR Doc. 04–22561 Filed 10–12–04; 8:45 am] 

BILLING CODE 4910–13–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. 2002–NM–294–AD; Amendment 

39–13820; AD 2004–20–15] 

RIN 2120–AA64 

Airworthiness Directives; Dornier 

Model 328–100 Series Airplanes

AGENCY: Federal Aviation 

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment supersedes 

an existing airworthiness directive (AD), 

applicable to all Dornier Model 328–100 

series airplanes, that currently requires 

certain revisions to the airplane flight 

manual, replacement of certain de-icing 

boots in the air intake duct assemblies 

of the engine with re-designed units, 

repetitive inspections of the boots to 

find discrepancies, and corrective action 

if necessary. This amendment also 

requires modification of the engine air 

inlet de-icing system. This action 

extends the repetitive inspection 

interval required by the existing AD, 

and adds repetitive debonding/

delamination and leakage inspections of 

the de-icing boots, and corrective action 

if necessary. Initiation of the extended 

repetitive inspections and new 

repetitive inspections ends the 

repetitive inspections required by the 

existing AD. The actions specified by 

this AD are intended to prevent engine 

malfunction due to failure of the engine 

air inlet de-icing system, which could 

result in reduced controllability of the 

airplane. This action is intended to 

address the identified unsafe condition.

DATES: Effective November 17, 2004. 

The incorporation by reference of 

certain publications, as listed in the 

regulations, is approved by the Director 

of the Federal Register as of November 

17, 2004. 

The incorporation by reference of 

certain other publications, as listed in 

the regulations, was approved 

previously by the Director of the Federal 

Register as of April 6, 1995 (60 FR 

15037, March 22, 1995).

ADDRESSES: The service information 

referenced in this AD may be obtained 

from AvCraft Aerospace GmbH, P.O. 

Box 1103, D–82230 Wessling, Germany. 

This information may be examined at 

the Federal Aviation Administration 

(FAA), Transport Airplane Directorate, 

Rules Docket, 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/

code_of_federal_regulations/

ibr_locations.html.

FOR FURTHER INFORMATION CONTACT: Tom 

Groves, Aerospace Engineer, 

International Branch, ANM–116, FAA, 

Transport Airplane Directorate, 1601 

Lind Avenue, SW., Renton, Washington 

98055–4056; telephone (425) 227–1503; 

fax (425) 227–1149.

SUPPLEMENTARY INFORMATION: A 

proposal to amend part 39 of the Federal 

Aviation Regulations (14 CFR part 39) 

by superseding AD 95–04–51, 

amendment 39–9179 (60 FR 15037, 

March 22, 1995), which is applicable to 

all Dornier Model 328–100 series 

airplanes, was published in the Federal 

Register on April 1, 2004 (69 FR 17097). 

The action proposed to continue to 

require the revisions to the AFM, 

replacement of certain de-icing boots in 

the air intake duct assemblies of the 

engine with re-designed units, and 

repetitive inspections of the boots to 

find discrepancies, and corrective action 

if necessary. The action also would 

require modification of the engine air 

inlet de-icing system, and would add a 

new AFM revision which changes the 

compliance time for the functional test 

required by the existing AD. The 

proposed action would extend the 

repetitive inspection interval required 

by the existing AD, and would add 

repetitive debonding/delamination and 

leakage inspections of the de-icing 

boots, and corrective action if necessary. 

Initiation of the extended repetitive 

inspections and new repetitive 

inspections would end the repetitive 

inspections required by the existing AD. 

Comments 

We provided the public the 

opportunity to participate in the 

development of this AD. No comments 

have been submitted in response to the 

proposed AD or on the determination of 

the cost to the public. 

Conclusion 

We have determined that air safety 

and the public interest require the 

adoption of the AD as proposed. 

Clarification of Inspection 

We have updated the definition of the 

detailed inspection in Note 1 of the AD 

to reflect our current definition. 

Cost Impact 

There are about 53 airplanes of U.S. 

registry that will be affected by this AD. 

The AFM revision currently required 

by AD 95–04–51 takes about 1 work 

hour per airplane to accomplish, at an 

average labor rate of $65 per work hour. 

Based on these figures, the cost impact 

of the currently required AFM revision 

is estimated to be $65 per airplane. 

The inspections currently required by 

AD 95–04–51 take about 1 work hour 

per airplane to accomplish, at an 

average labor rate of $65 per work hour. 

Based on these figures, the cost impact 

of the currently required inspections is 

estimated to be $65 per airplane, per 

inspection cycle. 

The replacement currently required 

by AD 95–04–51 takes about 5 work 

hours per airplane to accomplish, at an 

average labor rate of $65 per work hour. 

Required parts will cost about $55,000 

per airplane. Based on these figures, the 

cost impact of the currently required 

replacement is estimated to be $55,325 

per airplane.

The modification required in this AD 

action will take about 10 work hours per