56058 Federal Register / Vol. 71, No. 186 / Tuesday, September 26, 2006 / Proposed Rules 

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 

proposed AD would not have federalism 

implications under Executive Order 

13132. This proposed AD would 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 the proposed regulation: 

1. Is not a ‘‘significant regulatory 

action’’ under Executive Order 12866; 

2. Is not a ‘‘significant rule’’ under the 

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 proposed 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, Safety. 

The Proposed Amendment 

Accordingly, under the authority 

delegated to me by the Administrator, 

the FAA proposes to amend 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): 

Empresa Brasileira de Aeronautica S.A. 

(EMBRAER): FAA–2006–25892; 

Directorate Identifier 2006–NM–120–AD. 

Comments Due Date 

(a) The FAA must receive comments on 

this AD action by October 26, 2006. 

Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to all EMBRAER Model 

EMB–135BJ, –135ER, –135KE, –135KL, and 

–135LR airplanes; and Model EMB–145, 

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

and –145EP airplanes; certificated in any 

category. 

Unsafe Condition 

(d) This AD results from reports of smoke 

on the flight deck caused by damage from 

poor electrical contact due to loosening of the 

attaching hardware of the power cables of 

certain windshield temperature controllers. 

We are issuing this AD to prevent 

overheating of the power cable terminals of 

the windshield temperature controllers, 

which could result in smoke and fire on the 

flight deck. 

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. 

Inspecting for Part Number (P/N) of 

Controller 

(f) Within 5,000 flight hours after the 

effective date of this AD, inspect to 

determine the P/N of the left- and right-hand 

windshield temperature controllers. If any 

windshield temperature controller is found 

to have a P/N other than Goodrich P/N 

3801D2( ), no further action is required by 

this AD for that controller. 

Replacement of Attaching Hardware, 

Further Inspection, and Corrective Actions 

(g) Before further flight after performing the 

inspection required by paragraph (f) of this 

AD, for all windshield temperature 

controllers having Goodrich P/N 3801D2( ) 

or any controller for which the P/N cannot 

be conclusively determined: Replace the 

attaching hardware of the power cable 

terminals of the controllers with new, 

improved attaching hardware having new P/ 

Ns. Concurrently, perform a detailed 

inspection for signs of melting or damage of 

the plastic crimping ring, cable insulation, or 

terminals of the power cables, and, before 

further flight, perform applicable corrective 

actions. Perform all the actions in accordance 

with the Accomplishment Instructions of 

EMBRAER Service Bulletin 145–30–0043, 

Revision 02, dated May 25, 2006, or 

EMBRAER Service Bulletin 145LEG–30–

0013, dated June 28, 2005; as applicable. 

Credit for Actions Accomplished Using 

Previous Issue of Service Bulletin 

(h) Actions accomplished before the 

effective date of this AD in accordance with 

EMBRAER Service Bulletin 145–30–0043, 

dated June 28, 2005; or Revision 01, dated 

April 7, 2006; are considered acceptable for 

compliance with corresponding actions 

required by this AD. 

Alternative Methods of Compliance 

(AMOCs) 

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

ANM–116, has the authority to approve 

AMOCs for this AD, if requested in 

accordance with the procedures found in 14 

FR 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) Brazilian airworthiness directive 2006–

05–01, effective May 23, 2006, also addresses 

the subject of this AD. 

Issued in Renton, Washington, on 

September 14, 2006. 

Kalene C. Yanamura, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 06–8223 Filed 9–25–06; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2006–25890; Directorate 

Identifier 2006–NM–115–AD] 

RIN 2120–AA64 

Airworthiness Directives; Airbus Model 

A300 B2 and B4 Series Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: The FAA proposes to 

supersede an existing airworthiness 

directive (AD) that applies to all Airbus 

Model A300 B2, B4–100, and B4–200 

series airplanes. The existing AD 

currently requires supplemental 

structural inspections to detect fatigue 

cracking, and repair of cracked 

structure. This proposed AD would 

require revising the maintenance 

program by incorporating new and 

revised supplemental structural 

inspections, inspection intervals, and 

repairs; and repair of any damaged, 

cracked, or corroded structure; which 

would end the existing supplement 

structural inspections. This proposed 

AD results from a review of service 

history and reports received from the 

current supplemental structural 

inspection document program. We are 

proposing this AD to prevent reduced 

structural integrity of these airplanes 

due to fatigue cracking. 

DATES: We must receive comments on 

this proposed AD by October 26, 2006. 

ADDRESSES: Use one of the following 

addresses to submit comments on this 

proposed AD. 

• DOT Docket Web site: 

Go to http://dms.dot.gov and follow the 


sroberts on PROD1PC70 with PROPOSALS
Federal Register / Vol. 71, No. 186 / Tuesday, September 26, 2006 / Proposed Rules 56059 

instructions for sending your comments 

electronically. 

• Government-wide rulemaking Web 

site: Go to http://www.regulations.gov 

and follow the instructions for sending 

your comments electronically. 

• Mail: Docket Management Facility; 

U.S. Department of Transportation, 400 

Seventh Street, SW., Nassif Building, 

Room PL–401, Washington, DC 20590. 

• Fax: (202) 493–2251. 

• Hand Delivery: Room PL–401 on 

the plaza level of the Nassif Building, 

400 Seventh Street SW., Washington, 

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

through Friday, except Federal holidays. 

Contact Airbus, 1 Rond Point Maurice 

Bellonte, 31707 Blagnac Cedex, France, 

for service information identified in this 

proposed AD. 

FOR FURTHER INFORMATION CONTACT: Tom 

Stafford, Aerospace Engineer, 

International Branch, ANM–116, FAA, 

Transport Airplane Directorate, 1601 

Lind Avenue, SW., Renton, Washington 

98057–3356; telephone (425) 227–1622; 

fax (425) 227–1149. 

SUPPLEMENTARY INFORMATION: 

Comments Invited 

We invite you to submit any relevant 

written data, views, or arguments 

regarding this proposed AD. Send your 

comments to an address listed in the 

ADDRESSES section. Include the docket 

number ‘‘Docket No. FAA–2006–25890; 

Directorate Identifier 2006–NM–115–

AD’’ at the beginning of your comments. 

We specifically invite comments on the 

overall regulatory, economic, 

environmental, and energy aspects of 

the proposed AD. We will consider all 

comments received by the closing date 

and may amend the proposed AD in 

light of those comments. 

We will post all comments we 

receive, without change, to http:// 

dms.dot.gov, including any personal 

information you provide. We will also 

post a report summarizing each 

substantive verbal contact with FAA 

personnel concerning this proposed AD. 

Using the search function of that web 

site, anyone can find and read the 

comments in any of our dockets, 

including the name of the individual 

who sent the comment (or signed the 

comment on behalf of an association, 

business, labor union, etc.). You may 

review the DOT’s complete Privacy Act 

Statement in the Federal Register 

published on April 11, 2000 (65 FR 

19477–78), or you may visit http:// 

dms.dot.gov. 

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 DOT 

street address stated in the ADDRESSES

section. Comments will be available in 

the AD docket shortly after the Docket 

Management System receives them. 

Discussion 

On June 17, 1996, we issued AD 96–

13–11, amendment 39–9679 (61 FR 

35122, July 5, 1996), for all Airbus 

Model A300 B2, B4–100, and B4–200 

series airplanes. That AD requires 

supplemental structural inspections to 

detect fatigue cracking, and repair of 

cracked structure. That AD also requires 

revising the supplemental structural 

inspection document (SSID) program by 

changing some of the inspection 

techniques, changing some of the 

thresholds and intervals for inspections, 

expanding the area to be inspected for 

some of the inspections, and revising 

the Fleet Leader Program. That AD 

resulted from a review of service history 

and reports received from existing SSID 

inspections. We issued that AD to 

prevent reduced structural integrity of 

these airplanes due to fatigue cracking. 

Actions Since Existing AD Was Issued 

Since we issued AD 96–13–11, the 

European Aviation Safety Agency 

(EASA), which is the airworthiness 

authority for the European Union, 

notified us that an unsafe condition may 

exist on all Airbus Model A300 B2 and 

B4 series airplanes. The EASA advises 

that, based on a review of service 

history and reports received from the 

current SSID program, further 

rulemaking is necessary in order to 

ensure the continued structural integrity 

of these airplanes. 

Relevant Service Information 

Airbus has issued A300 

Airworthiness Limitation Items (ALI) 

Document SEM2/95A.1090/05, Issue 3, 

dated September 2005 (hereafter 

referred to as ‘‘Issue 3 of the ALI’’). Issue 

3 of the ALI defines inspections and 

modifications necessary to ensure the 

structural integrity applicable to the 

specified threshold (structural 

modification point) arising from the 

evaluation of widespread fatigue 

damage, and fatigue-related 

supplemental structural inspections for 

a given applicability period from zero 

flight cycles/flight hours to the limit of 

validity. 

Airbus also has issued Temporary 

Revision (TR) 3.1, dated April 2006 

(hereafter referred to as ‘‘TR 3.1’’), of 

Issue 3 of the ALI. TR 3.1 contains 

changes and additions to Issue 3 of the 

ALI. The applicability, limit of validity, 

program rules, program notes, and 

definitions remain valid as stated in 

Issue 3 of the ALI. 

Accomplishing the actions specified 

in Issue 3 of the ALI as revised by TR 

3.1 ends the supplemental structural 

inspections required by AD 96–13–11. 

Accomplishing the actions specified 

in the service information is intended to 

adequately address the unsafe 

condition. The EASA mandated the 

service information and issued 

airworthiness directive 2006–0071, 

dated March 30, 2006, to ensure the 

continued airworthiness of these 

airplanes in the European Union. 

FAA’s Determination and Requirements 

of the Proposed AD 

These airplane models are 

manufactured in France and are type 

certificated for operation in the United 

States under the provisions of section 

21.29 of the Federal Aviation 

Regulations (14 CFR 21.29) and the 

applicable bilateral airworthiness 

agreement. As described in FAA Order 

8100.14A, ‘‘Interim Procedures for 

Working with the European Community 

on Airworthiness Certification and 

Continued Airworthiness,’’ dated 

August 12, 2005, the EASA has kept the 

FAA informed of the situation described 

above. We have examined the EASA’s 

findings, evaluated all pertinent 

information, and determined that we 

need to issue an AD for products of this 

type design that are certificated for 

operation in the United States. 

This proposed AD would supersede 

AD 96–13–11 and would retain all the 

requirements of the existing AD. This 

proposed AD would also require 

revising the FAA-approved maintenance 

program by incorporating new and 

revised supplemental structural 

inspections, inspection intervals, and 

repairs; and repair of any damaged, 

cracked, or corroded structure; which 

would end the existing supplement 

structural inspections. 

Differences Between the Proposed AD, 

EASA Airworthiness Directive, Issue 3 

of the ALI, and TR 3.1 

The EASA airworthiness directive 

specifies a compliance time of within 90 

days from the effective date of the 

airworthiness directive for doing the 

actions specified in Issue 3 of the ALI, 

which replaces the actions specified in 

Airbus A300 SSID, Revision 4. 

However, this proposed AD would 

require, within 12 months after the 

effective date of this AD, revising the 


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56060 Federal Register / Vol. 71, No. 186 / Tuesday, September 26, 2006 / Proposed Rules 

FAA-approved maintenance program by 

incorporating the new and revised 

actions specified in Issue 3 of the ALI 

as revised by TR 3.1. In developing an 

appropriate compliance time for this 

action, we considered the safety 

implications and normal maintenance 

schedules for the timely 

accomplishment of the proposed 

revision. We also consider the proposed 

revision to be more complex than that 

required by the EASA airworthiness 

directive. AD 96–13–11 did not mandate 

incorporation of Revision 3 or Revision 

4 of the Airbus A300 SSID and thus U.S. 

operators would be required to 

incorporate more changes than those 

specified in the EASA airworthiness 

directive. In consideration of these 

items, we have determined that a 

compliance time of 12 months will 

ensure an acceptable level of safety and 

allow the revision to be done during 

scheduled maintenance intervals for 

most affected operators. 

Unlike the procedures described in 

Issue 3 of the ALI as revised by TR 3.1, 

this proposed AD would not permit 

further flight if any cracked structure is 

detected. We have determined that, 

because of the safety implications and 

consequences associated with that 

cracking, any cracked structure must be 

repaired before further flight. This 

difference has been coordinated with 

the EASA. 

Issue 3 of the ALI as revised by TR 3.1 

specifies to contact the manufacturer for 

instructions on how to repair certain 

conditions, but this proposed AD would 

require repairing those conditions using 

a method that we or the EASA (or its 

delegated agent) approve. In light of the 

type of repair that would be required to 

address the unsafe condition, and 

consistent with existing bilateral 

airworthiness agreements, we have 

determined that, for this proposed AD, 

a repair we or the EASA approve would 

be acceptable for compliance with this 

proposed AD. 

Although Issue 3 of the ALI as revised 

by TR 3.1 specifies a ‘‘Sampling 

Concept’’ in section B, this proposed AD 

does not include that requirement. 

Since issuance of AD 98–16–06, we 

have determined that such a sampling 

does not provide an adequate statistical 

sampling size to provide confidence in 

the structural integrity of the fleet of 

airplanes. Therefore, the proposed AD 

would prohibit the use of such a 

sampling program and would require all 

affected airplanes of the fleet to be 

inspected. 

Change to Existing AD 

This proposed AD would retain all 

requirements of AD 96–13–11. Since AD 

96–13–11 was issued, the AD format has 

been revised, and certain paragraphs 

have been rearranged. As a result, the 

corresponding paragraph identifiers 

have changed in this proposed AD, as 

listed in the following table: 

REVISED PARAGRAPH IDENTIFIERS

Requirement in AD 

96–13–11 

Corresponding requirement in this proposed AD 

paragraph (a) ............ paragraph (f). 

paragraph (b) ............ paragraph (g). 

paragraph (c) ............ paragraph (h). 

paragraph (d) ............ paragraph (i). 

paragraph (e) ............ paragraph (j). 

paragraph (f) ............. paragraph (k). 

paragraph (g) ............ paragraph (l). 

paragraph (h) ............ paragraph (m). 

paragraph (i) ............. paragraph (n). 

paragraph (j) ............. paragraph (o). 

paragraph (k) ............ paragraph (p). 

paragraph (l) ............. paragraph (q). 

Costs of Compliance 

The following table provides the 

estimated costs for U.S. operators to 

comply with this proposed AD. 

ESTIMATED COSTS

Action Work 

hours 

Average 

labor rate per 

hour 

Parts Cost per 

airplane 

Number 

of U.S.- 

registered 

airplanes 

Fleet cost 

Implementation of SSID (required by AD 96–13–11) .................. 597 $80 None $47,760 29 $1,385,040 

Revision of the FAA-approved maintenance program (new proposed action).10 80 None 800 29 23,200 

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 

proposed AD would not have federalism 

implications under Executive Order 

13132. This proposed AD would 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 the proposed regulation: 

1. Is not a ‘‘significant regulatory 

action’’ under Executive Order 12866; 

2. Is not a ‘‘significant rule’’ under the 

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 proposed 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, Safety. 

The Proposed Amendment 

Accordingly, under the authority 

delegated to me by the Administrator, 

the FAA proposes to amend 14 CFR part 

39 as follows: 

PART 39—AIRWORTHINESS 

DIRECTIVES 

1. The authority citation for part 39 

continues to read as follows: 


sroberts on PROD1PC70 with PROPOSALS
Federal Register / Vol. 71, No. 186 / Tuesday, September 26, 2006 / Proposed Rules 56061 

Authority: 49 U.S.C. 106(g), 40113, 44701. 

§ 39.13 [Amended] 

2. The Federal Aviation 

Administration (FAA) amends § 39.13 

by removing amendment 39–9679 (61 

FR 35122, July 5, 1996) and adding the 

following new airworthiness directive 

(AD): 

Airbus: Docket No. FAA–2006–25890; 

Directorate Identifier 2006–NM–115–AD. 

Comments Due Date 

(a) The FAA must receive comments on 

this AD action by October 26, 2006. 

Affected ADs 

(b) This AD supersedes AD 96–13–11. 

Applicability 

(c) This AD applies to all Airbus Model 

A300 B2 and B4 series airplanes, certificated 

in any category. 

Note 1: This AD requires revisions to 

certain operator maintenance documents to 

include new inspections. Compliance with 

these inspections is required by 14 CFR 

91.403(c). For airplanes that have been 

previously modified, altered, or repaired in 

the areas addressed by these inspections, the 

operator may not be able to accomplish the 

inspections described in the revisions. In this 

situation, to comply with 14 CFR 91.403(c), 

the operator must request approval for an 

alternative method of compliance according 

to paragraph (x) of this AD. The request 

should include a description of changes to 

the required inspections that will ensure the 

continued damage tolerance of the affected 

structure. The FAA has provided guidance 

for this determination in Advisory Circular 

(AC) 25–1529. 

Unsafe Condition 

(d) This AD results from a review of service 

history and reports received from the current 

supplemental structural inspection document 

program. We are issuing this AD to prevent 

reduced structural integrity of these airplanes 

due to fatigue cracking. 

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. 

Requirements of AD 96–13–11: 

(f) Within one year after March 9, 1993 (the 

effective date of AD 93–01–24, amendment 

39–8478), incorporate a revision into the 

FAA-approved maintenance inspection 

program that provides for supplemental 

maintenance inspections, modifications, 

repair, or replacement of the significant 

structural details (SSD) and significant 

structural items (SSI) specified in ‘‘Airbus 

Industrie A300 Supplemental Structural 

Inspection Document’’ (SSID), dated 

September 1989 (hereafter referred to as ‘‘the 

SSID’’). 

(g) Within one year after August 9, 1996 

(the effective date of AD 96–13–11), replace 

the revision of the FAA-approved 

maintenance program required by paragraph 

(f) of this AD with the inspections, inspection 

intervals, repairs, and replacements defined 

in ‘‘Airbus Industrie A300 Supplemental 

Structural Inspection Document’’ (SSID), 

Revision 2, dated June 1994 (hereafter 

referred to as ‘‘Revision 2 of the SSID’’). 

Accomplish the actions specified in the 

service bulletins identified in Section 6, ‘‘SB 

Reference List,’’ Revision 2 of the SSID, at the 

times specified in those service bulletins. 

The actions are to be accomplished in 

accordance with those service bulletins. 

(1) For airplanes that have exceeded the 

threshold specified in any of the service 

bulletins identified in Section 6, ‘‘SB 

Reference List,’’ Revision 2 of the SSID: 

Accomplish the actions specified in those 

service bulletins within the grace period 

specified in that service bulletin. The grace 

period is to be measured from August 9, 

1996. 

(2) For airplanes that have exceeded the 

threshold specified in any of the service 

bulletins identified in Section 6, ‘‘SB 

Reference List,’’ Revision 2 of the SSID, and 

a grace period is not specified in that service 

bulletin: Accomplish the actions specified in 

that service bulletin within 1,500 flight 

cycles after August 9, 1996. 

(h) If any cracked structure is detected 

during the inspections required by either 

paragraph (f) or (g) of this AD, prior to further 

flight, permanently repair the cracked 

structure in accordance with either paragraph 

(h)(1), (h)(2), or (h)(3) of this AD. 

Note 2: A permanent repair is defined as 

a repair that meets the certification basis of 

the airplane, and does not require additional 

modification at a later date. 

(1) The service bulletins listed in Section 

6, ‘‘SB Reference List,’’ of the SSID (for 

airplanes that are currently being inspected 

in accordance with paragraph (f) of this AD); 

or in accordance with a method approved by 

the Manager, International Branch, ANM–116 

(formerly the Standardization Branch, ANM–

113), FAA, Transport Airplane Directorate, if 

a permanent repair is not specified in any of 

these service bulletins. Or 

(2) The service bulletins listed in Section 

6, ‘‘SB Reference List,’’ of Revision 2 of the 

SSID (for airplanes that are currently being 

inspected in accordance with paragraph (g) of 

this AD); or in accordance with a method 

approved by the Manager, International 

Branch, ANM–116 (formerly the 

Standardization Branch, ANM–113), if a 

permanent repair is not specified in any of 

these service bulletins. Or 

(3) Other permanent repair data meeting 

the certification basis of the airplane which 

is approved by the Manager, International 

Branch, ANM–116 (formerly the 

Standardization Branch, ANM–113), or by 

the Direction Gea ́nea ́rale de l’Aviation Civile 

(DGAC) of France. 

(i) For airplanes identified as Fleet Leader 

Program (FLP) in Section 5, ‘‘Fleet Leader 

Program,’’ of the SSID or Revision 2 of the 

SSID: Inspect according to the instructions 

and intervals specified in paragraph 4.4, 

‘‘Adjustment of Inspection Requirements and 

DSG,’’ of Section 4, or Section 9, as 

applicable, of the SSID (for airplanes 

inspected in accordance with paragraph (f) of 

this AD), or Revision 2 of the SSID (for 

airplanes inspected in accordance with 

paragraph (g) of this AD), for each SSD. 

(j) For the purpose of accomplishing 

paragraphs (i), (k), (l), and (n) of this AD, 

operators shall not use paragraph 6.2, 

‘‘Complete RR Method,’’ of Section 9 of the 

SSID to calculate inspection thresholds and 

intervals. 

(k) For Model A300–B2 and B2K–3C series 

airplanes: For any SSD that has exceeded the 

values of the threshold specified in 

paragraph 6, ‘‘Inspection Threshold and 

Intervals,’’ Section 9 of the SSID, inspect at 

the time specified in either paragraph (k)(1) 

or (k)(2) of this AD, as applicable. 

(1) For airplanes inspected in accordance 

with paragraph (f) of this AD: Inspect within 

2,000 landings after March 9, 1993, in 

accordance with the SSID. Or 

(2) For airplanes inspected in accordance 

with paragraph (g) of this AD: Inspect within 

2,000 landings after August 9, 1996, in 

accordance with Revision 2 of the SSID. 

(l) For Model A300–B4 series airplanes: 

For any SSD that has exceeded the values of 

the threshold specified in paragraph 6, 

‘‘Inspection Threshold and Intervals,’’

Section 9 of the SSID, inspect at the time 

specified in either paragraph (l)(1) or (l)(2) of 

this AD, as applicable. 

(1) For airplanes inspected in accordance 

with paragraph (f) of this AD: Inspect within 

1,500 landings after March 9, 1993 [the 

effective date of AD 93–01–24, amendment 

39–8478]. Or 

(2) For airplanes inspected in accordance 

with paragraph (g) of this AD: Inspect within 

1,500 landings after August 9, 1996. 

(m) For airplanes identified as FLP in 

Section 5, ‘‘Fleet Leader Program,’’ of the 

SSID or Revision 2 of the SSID: Within one 

year after August 9, 1996, apply the basic 

requirements given in Revision 2 of the SSID. 

(n) For airplanes that are subject to the 

requirements of paragraph (g) of this AD, and 

have exceeded the initial inspection 

threshold specified in paragraph 4.4, 

‘‘Adjustment of Inspection Requirements and 

DSG,’’ of Section 4, or paragraph 6, 

‘‘Inspection Threshold and Intervals,’’ of 

Section 9, for each SSD: Perform the initial 

inspection prior to the accumulation of the 

number of flight cycles specified in 

paragraph 7, ‘‘Additional Information,’’

Section 9, of Revision 2 of the SSID. 

Note 3: Fatigue ratings are not applicable 

to these allowances; therefore, no adjustment 

is required. 

Note 4: Paragraph (n) of this AD provides 

the ‘‘grace’’ periods for those airplanes that 

are new to the FLP or that have newly added 

or revised SSID requirements in accordance 

with paragraph (g) of this AD. 

(o) The grace period provided by paragraph 

(n) of this AD is also applicable to the 

thresholds and/or repeat intervals for each 

SSD for which the inspection interval or 

threshold was reduced in accordance with 

the requirements of paragraph (g) of this AD. 

(p) For FLP airplanes identified in Section 

5, ‘‘Fleet Leader Program,’’ of the SSID or 

Revision 2 of the SSID that are listed in 

Section 7, ‘‘SSI Limitation List,’’ of the SSID 

(for airplanes that are currently being 

inspected in accordance with paragraph (f) of 

this AD) , or Revision 2 of the SSID (for 

airplanes that are currently being inspected 

in accordance with paragraph (g) of this AD): 


sroberts on PROD1PC70 with PROPOSALS
56062 Federal Register / Vol. 71, No. 186 / Tuesday, September 26, 2006 / Proposed Rules 

Inspect at intervals not to exceed the interval 

specified for each SSI, in accordance with the 

values given in Section 7, ‘‘SSI Limitation 

List,’’ of the SSID or Revision 2 of the SSID, 

as applicable. 

(q) For all airplanes: All inspection results, 

positive or negative, must be reported to 

Airbus in accordance with either paragraph 

(q)(1) or (q)(2) of this AD, as applicable. 

Information collection requirements 

contained in this regulation have been 

approved by the Office of Management and 

Budget (OMB) under the provisions of the 

Paperwork Reduction Act of 1980 (44 U.S.C. 

3501 et seq.) and have been assigned OMB 

Control Number 2120–0056. 

(1) For FLP airplanes, identified in Section 

5, ‘‘Fleet Leader Program,’’ of the SSID or 

Revision 2 of the SSID: Submit reports in 

accordance with the instructions in 

paragraph 5.2, ‘‘SSIP Inspection Reporting,’’

of Section 5, and paragraph 7.1, ‘‘General,’’

of Section 7 of the SSID (for airplanes that 

are currently being inspected in accordance 

with paragraph (f) of this AD); or Revision 2 

of the SSID (for airplanes inspected in 

accordance with paragraph (g) of this AD). 

(2) For all airplanes that are subject to 

Section 6, ‘‘SB Reference List,’’ of the SSID: 

Submit reports in accordance with the 

instructions in the applicable service 

bulletins identified in Section 6 of the SSID 

(for airplanes that are currently being 

inspected in accordance with paragraph (f) of 

this AD); or Revision 2 of the SSID (for 

airplanes that are currently being inspected 

in accordance with paragraph (g) of this AD). 

New Requirements of This AD 

Revision of the FAA-Approved Maintenance 

Inspection Program 

(r) Within 12 months after the effective 

date of this AD, replace the revision of the 

FAA-approved maintenance program 

required by paragraph (g) of this AD with the 

supplemental structural inspections, 

inspection intervals, and repairs defined in 

Airbus A300 Airworthiness Limitation Items 

(ALI) Document SEM2/95A.1090/05, Issue 3, 

dated September 2005, as revised by Airbus 

Temporary Revision (TR) 3.1, dated April 

2006 (hereafter referred to as ‘‘Issue 3 of the 

ALI’’). Accomplish the actions specified in 

Issue 3 of the ALI at the times specified in 

that ALI, except as provided by paragraph (s) 

of this AD. The actions must be 

accomplished in accordance with Issue 3 of 

the ALI. Accomplishing the applicable initial 

ALI tasks constitutes terminating action for 

the requirements of paragraphs (f) through (q) 

of this AD. 

(s) For airplanes that have exceeded the 

threshold or intervals specified in Issue 3 of 

the ALI for the application tolerance on the 

first interval for new and revised 

requirements and have exceeded 50 percent 

of the intervals specified in sections D and 

E of Issue 3 of the ALI: Do the actions within 

6 months after the effective date of this AD. 

Corrective Actions 

(t) Damaged, cracked, or corroded structure 

detected during any inspection done in 

accordance with Issue 3 of the ALI must be 

repaired, before further flight, in accordance 

with Issue 3 of the ALI, except as provided 

by paragraph (u) of this AD; or other data 

meeting the certification basis of the airplane 

which is approved by the Manager, 

International Branch, ANM–116; or by the 

European Aviation Safety Agency (EASA) (or 

its delegated agent). 

(u) Where Issue 3 of the ALI specifies 

contacting Airbus for appropriate action: 

Before further flight, repair the damaged, 

cracked, or corroded structure using a 

method approved by either the Manager, 

International Branch, ANM–116; or the 

EASA (or its delegated agent). 

No Fleet Sampling 

(v) Although Issue 3 of the ALI specifies to 

do a ‘‘Sampling Concept’’ in section B, this 

AD prohibits the use of such a sampling 

program and requires all affected airplanes of 

the fleet to be inspected. 

No Reporting 

(w) Although Issue 3 of the ALI specifies 

to submit certain information to the 

manufacturer, this AD does not include that 

requirement. 

Alternative Methods of Compliance 

(AMOCs) 

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

ANM–116 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. 

(3) AMOCs approved previously in 

accordance with AD 96–13–11 are approved 

as AMOCs for the corresponding provisions 

of paragraphs (f) through (q) of this AD. 

Related Information 

(y) The EASA airworthiness directive 

2006–0071, dated March 30, 2006, also 

addresses the subject of this AD. 

Issued in Renton, Washington, on 

September 14, 2006. 

Kalene C. Yanamura, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 06–8224 Filed 9–25–06; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2006–25889; Directorate 

Identifier 2006–NM–168–AD] 

RIN 2120–AA64 

Airworthiness Directives; Empresa 

Brasileira de Aeronautica S.A. 

(EMBRAER) Model ERJ 170 Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: The FAA proposes to adopt a 

new airworthiness directive (AD) for 

certain EMBRAER Model ERJ 170 

airplanes. This proposed AD would 

require replacement of certain electrical 

bonding clamps and attaching hardware 

with new or serviceable parts, as 

applicable, and other specified action. 

This proposed AD results from failure of 

an electrical bonding clamp, used to 

attach the electrical bonding straps to 

the fuel system lines. We are proposing 

this AD to prevent loss of bonding 

protection in the interior of the fuel 

tanks or adjacent areas that, in 

combination with lightning strike, could 

result in a fuel tank explosion and 

consequent loss of the airplane. 

DATES: We must receive comments on 

this proposed AD by October 26, 2006. 

ADDRESSES: Use one of the following 

addresses to submit comments on this 

proposed AD. 

• DOT Docket Web site: Go to http:// 

dms.dot.gov and follow the instructions 

for sending your comments 

electronically. 

• Government-wide rulemaking Web 

site: Go to http://www.regulations.gov 

and follow the instructions for sending 

your comments electronically. 

• Mail: Docket Management Facility, 

U.S. Department of Transportation, 400 

Seventh Street, SW., Nassif Building, 

room PL–401, Washington, DC 20590. 

• Fax: (202) 493–2251. 

• Hand Delivery: Room PL–401 on 

the plaza level of the Nassif Building, 

400 Seventh Street, SW., Washington, 

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

through Friday, except Federal holidays. 

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 proposed 

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: 

Comments Invited 

We invite you to submit any relevant 

written data, views, or arguments 

regarding this proposed AD. Send your 

comments to an address listed in the 

ADDRESSES section. Include the docket 

number ‘‘FAA–2006–25889; Directorate 

Identifier 2006–NM–168–AD’’ at the 

beginning of your comments. We 


sroberts on PROD1PC70 with PROPOSALS