Federal Register / Vol. 71, No. 24 / Monday, February 6, 2006 / Rules and Regulations 5971 

crack using a method approved in 

accordance with the procedures specified in 

paragraph (k) of this AD. 

Optional Preventive Modification 

(h) Installing an external doubler on a 

corner in accordance with the 

Accomplishment Instructions of Boeing 

Service Bulletin DC8–53–079, Revision 01, 

dated June 26, 2002, terminates the repetitive 

inspection intervals of paragraph (f) of this 

AD for that corner. Before the accumulation 

of 17,000 flight cycles after the installation: 

Do the next inspection of that corner, as 

specified in paragraph (f) of this AD. Repeat 

the inspections in paragraph (f) of this AD for 

that corner thereafter at intervals not to 

exceed 4,400 flight cycles. 

No Reporting Required 

(i) Although the service bulletin referenced 

in this AD specifies to submit certain 

information to the manufacturer, this AD 

does not include that requirement. 

Actions Accomplished In Accordance With 

Previous Issue of Service Bulletin 

(j) Actions accomplished before the 

effective date of this AD in accordance with 

McDonnell Douglas Service Bulletin C8–53–

079, dated January 31, 2001, are acceptable 

for compliance with the corresponding action 

in this AD. 

Alternative Methods of Compliance 

(AMOCs) 

(k)(1) The Manager, Los Angeles Aircraft 

Certification Office (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) 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) An AMOC that provides an acceptable 

level of safety may be used for any repair 

required by this AD, if it is approved by an 

Authorized Representative for the Boeing 

Commercial Airplanes Delegation Option 

Authorization Organization who has been 

authorized by the Manager, Los Angeles 

ACO, to make those findings. For a repair 

method to be approved, the repair must meet 

the certification basis of the airplane and 14 

CFR 25.571, Amendment 45, and the 

approval must specifically refer to this AD. 

(4) Inspections required by this AD of 

specified areas of Principal Structural 

Element (PSE) 53.08.044 are acceptable for 

compliance with the applicable requirements 

of paragraphs (a) and (b) of AD 93–01–15, 

amendment 39–8469 (58 FR 5576, January 

22, 1993). The remaining areas of the affected 

PSEs must be inspected and repaired as 

applicable, in accordance with AD 93–01–15. 

Material Incorporated by Reference 

(l) You must use Boeing Service Bulletin 

DC8–53–079, Revision 01, dated June 26, 

2002, 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 Boeing Commercial Airplanes, Long 

Beach Division, 3855 Lakewood Boulevard, 

Long Beach, California 90846, Attention: 

Data and Service Management, Dept. C1–L5A 

(D800–0024), 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 January 

24, 2006. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 06–987 Filed 2–3–06; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2005–21702; Directorate 

Identifier 2005–NM–024–AD; Amendment 

39–14473; AD 2006–03–09] 

RIN 2120–AA64 

Airworthiness Directives; Airbus Model 

A330–200 and –300 Series Airplanes, 

A340–200 and –300 Series Airplanes, 

and A340–541 and –642 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 

Airbus Model A330–200 and –300 series 

airplanes, A340–200 and –300 series 

airplanes, and A340–541 and –642 

airplanes. This AD requires repetitive 

borescope inspections of the left and 

right fuel tanks of the trimmable 

horizontal stabilizers (trim tanks) for 

detached or damaged float valves; 

related investigative/corrective actions 

if necessary; and the eventual 

replacement of all float valves in the left 

and right trim tanks with new, 

improved float valves, which terminates 

the need for the repetitive inspections. 

This AD also requires repetitive 

replacement of certain new, improved 

float valves. This AD results from 

reports of detached and damaged float 

valves in the trim tanks. We are issuing 

this AD to prevent, in the event of a 

lightning strike to the horizontal 

stabilizer, sparking of metal parts and 

debris from detached and damaged float 

valves, or a buildup of static electricity, 

which could result in ignition of fuel 

vapors and consequent fire or explosion. 

DATES: This AD becomes effective 

March 13, 2006. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in the AD 

as of March 13, 2006. 

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 Airbus, 1 Rond Point Maurice 

Bellonte, 31707 Blagnac Cedex, France, 

for service information identified in this 

AD. 

FOR FURTHER INFORMATION CONTACT: Tim 

Backman, Aerospace Engineer, 

International Branch, ANM–116, FAA, 

Transport Airplane Directorate, 1601 

Lind Avenue, SW., Renton, Washington 

98055–4056; telephone (425) 227–2797; 

fax (425) 227–1149. 

SUPPLEMENTARY INFORMATION: 

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 Airbus Model A330 and 

A340 series airplanes. That NPRM was 

published in the Federal Register on 

June 29, 2005 (70 FR 37296). That 

NPRM proposed to require repetitive 

borescope inspections of the left and 

right fuel tanks of the trimmable 

horizontal stabilizers (trim tanks) for 

detached or damaged float valves; 

related investigative/corrective actions 

if necessary; and the eventual 

replacement of all float valves in the left 

and right trim tanks with new, 

improved float valves, which terminates 

the need for the repetitive inspections. 

That NPRM also proposed to require 

repetitive replacement of certain new, 

improved float valves. 


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5972 Federal Register / Vol. 71, No. 24 / Monday, February 6, 2006 / Rules and Regulations 

Comments 

We provided the public the 

opportunity to participate in the 

development of this AD. We have 

considered the comments received. 

Requests That Resulted in a Change to 

the NPRM 

Request To Add Another Service 

Bulletin 

One commenter requests that the 

NPRM reference an additional service 

bulletin. The commenter explains that 

Airbus Service Bulletin A330–28–3093, 

dated June 16, 2005, installs the same 

Airbus modification number (53081) as 

Airbus Service Bulletin A330–28–3094, 

dated April 7, 2005, which was 

referenced in the NPRM as an 

appropriate source of service 

information. The commenter explains 

that the effectivity in Airbus Service 

Bulletin A330–28–3093 includes all of 

the commenter’s airplanes, while Airbus 

Service Bulletin A330–28–3094 does 

not. 

We agree to add Airbus Service 

Bulletin A330–28–3093 as another 

method of compliance to the 

requirements of the AD. We note that 

adding this service bulletin is for the 

convenience of the operator in 

accomplishing the actions required by 

this AD, and does not add or remove 

any airplane listed in the applicability 

of this AD. 

Request To Revise the Costs of 

Compliance 

The same commenter requests that the 

NPRM be revised to add an estimated 

cost for access to each of the valves 

during replacement of the valves, which 

is a terminating action. The commenter 

notes that the service information 

estimates a total of 76 hours of access 

related labor time. The commenter 

estimates a more realistic value to be 

116 hours. The commenter recognizes 

that access time is typically not 

included in the labor estimates of ADs. 

However, the commenter advises that 

there are no tasks in the A330 

maintenance program that require 

access to this area. Therefore, the access 

hours will be driven solely and 

specifically by the NPRM. 

We agree that, in this case, it is 

appropriate to consider the time 

necessary for access. We also recognize 

that different operators may have 

different access times based on different 

airplane configurations or other 

considerations. The estimated cost 

information for access that is provided 

by the manufacturer is the latest 

information that we have, and we have 

revised the AD to reflect that estimate. 

Requests That Did Not Result in a 

Change to the NPRM 

Request To Address Defective Parts 

Manufacturer Approval (PMA) Parts 

One commenter requests that the 

NPRM be modified to include possible 

‘‘defective’’ parts manufactured with a 

parts manufacturer approval (PMA) that 

may be installed in lieu of the defective 

original equipment manufacturer (OEM) 

part specified in the NPRM. The 

commenter states that a ‘‘known’’ PMA 

part exists for the defective OEM part 

specified in the NPRM, and may contain 

the same defects as the specified OEM 

part. The commenter further points out 

that, if a PMA part is defective and 

currently installed, the NPRM would 

not require its removal. 

We concur with the commenter’s 

general request that, if we know that an 

unsafe condition also exists in PMA 

parts, the AD should address those 

parts, as well as the original parts. 

Contrary to the commenter’s assertion 

that the known PMA part is not covered 

by the wording of the NPRM, the 

‘‘known’’ PMA part identified by the 

commenter does have the same part 

number as the part number specified in 

the NPRM. Therefore, it is also subject 

to the requirements of this AD. We are 

not aware of other PMA parts that may 

have a different part number. The 

commenter’s remarks are timely in that 

the Transport Airplane Directorate 

currently is in the process of reviewing 

this issue as it applies to transport 

category airplanes. We acknowledge 

that there may be other ways of 

addressing this issue to ensure that 

unsafe PMA parts are identified and 

addressed. Once we have thoroughly 

examined all aspects of this issue, 

including input from industry, and have 

made a final determination, we will 

consider whether our policy regarding 

addressing PMA parts in ADs needs to 

be revised. We consider that to delay 

this AD action would be inappropriate, 

since we have determined that an 

unsafe condition exists and that 

replacement of certain parts must be 

accomplished to ensure continued 

safety. Therefore, no change has been 

made to the final rule in this regard. 

Request to Reference PMA Parts 

The same commenter also requests 

that the language in the NPRM be 

changed to permit installation of PMA 

equivalent parts. The commenter states 

that the mandated installation of a 

certain part number in the NPRM ‘‘is at 

variance with the higher authority of 14 

CFR Section 21.303.’’

We infer that the commenter would 

like the AD to permit installation of any 

equivalent PMA parts so that it is not 

necessary for an operator to request 

approval of an alternative method of 

compliance (AMOC) in order to install 

an ‘‘equivalent’’ PMA part. Whether an 

alternative part is ‘‘equivalent’’ in 

adequately resolving the unsafe 

condition can only be determined on a 

case-by-case basis based on a complete 

understanding of the unsafe condition. 

We are not currently aware of any such 

parts. Our policy is that, in order for 

operators to replace a part with one that 

is not specified in the AD, they must 

request an AMOC. This is necessary so 

that we can make a specific 

determination that an alternative part is 

or is not susceptible to the same unsafe 

condition. 

In response to the commenter’s 

statement regarding a ‘‘variance with 

FAR 21.303,’’ under which the FAA 

issues PMAs, this statement appears to 

reflect a misunderstanding of the 

relationship between ADs and the 

certification procedural regulations of 

part 21 of the FARs (14 CFR part 21). 

Those regulations, including section 

21.303 of the FARs (14 CFR part 

21.303), are intended to ensure that 

aeronautical products comply with the 

applicable airworthiness standards. But 

ADs are issued when, notwithstanding 

those procedures, we become aware of 

unsafe conditions in these products or 

parts. Therefore, an AD takes 

precedence over design approvals when 

we identify an unsafe condition, and 

mandating installation of a certain part 

number in an AD is not at variance with 

section § 21.303. 

The AD provides a means of 

compliance for operators to ensure that 

the identified unsafe condition is 

addressed appropriately. For an unsafe 

condition attributable to a part, the AD 

normally identifies the replacement 

parts necessary to obtain that 

compliance. As stated in section 39.7 of 

the FARs (14 CFR 39.7), ‘‘Anyone who 

operates a product that does not meet 

the requirements of an applicable 

airworthiness directive is in violation of 

this section.’’ Unless an operator obtains 

approval for an AMOC, replacing a part 

with one not specified by the AD would 

make the operator subject to an 

enforcement action and result in a civil 

penalty. No change to the AD is 

necessary in this regard. 

Editorial Changes to the AD 

Clarification of Alternative Method of 

Compliance (AMOC) Paragraph 

We have revised this action to clarify 

the appropriate procedure for notifying 

the principal inspector before using any 


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Federal Register / Vol. 71, No. 24 / Monday, February 6, 2006 / Rules and Regulations 5973 

approved AMOC on any airplane to 

which the AMOC applies. 

Explanation of Change to Applicability 

We have revised the applicability of 

the existing AD to identify model 

designations as published in the most 

recent type certificate data sheet for the 

affected models. 

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, at an average labor rate 

per hour of $65, for U.S. operators of 

Model A330–200 and –300 series 

airplanes to comply with this AD. 

ESTIMATED COSTS

Action Work hours Parts Cost per 

airplane 

Number of 

U.S. registered 

airplanes 

Fleet cost 

Repetitive borescope inspection, per 

inspection cycle.

2 hours for inspection ....................... None ........ $130 25 $3,250, per inspection 

cycle. 

Installation of float valves (including 

access).

4 hours (2 per valve, 2 valves per 

airplane) plus 76 hours for access.

No charge 5,200 25 $130,000, per installation. 

Bonding test (new, improved float 

valves, left trim tank only).

1 ........................................................ None ........ 65 25 $1,625. 

Currently, there are no affected Model 

A340–200 and –300 series airplanes and 

A340–541 and –642 airplanes on the 

U.S. Register. However, should an 

affected airplane be imported and 

placed on the U.S. Register in the future, 

it would be subject to the actions of this 

AD. The estimated costs would be the 

same as those listed above for the Model 

A330–200 and –300 series airplanes. 

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): 

2006–03–09 Airbus: Amendment 39–

14473. Docket No. FAA–2005–21702; 

Directorate Identifier 2005–NM–024–AD. 

Effective Date 

(a) This AD becomes effective March 13, 

2006. 

Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to Airbus Model A330–

201, –202, –203, –223, –243, –301, –321, 

–322, –323, –341, –342, and –343 airplanes; 

and A340–211, –212, –213 –311, –312, –313, 

–541, and –642 airplanes; certificated in any 

category, as identified in Table 1 of this AD. 

TABLE 1.—APPLICABILITY

Airbus model Except those modified in production by Airbus modification 

A330–201, –202, –203, –223, –243, –301, –321, –322, –323, –341, 

–342, and –343 airplanes.

51953 and either 52110 or 53081. 

A340–211, –212, –213, –311, –312, –313 airplanes ............................... 51953 and either 52110 or 53081. 

A340–541 and –642 airplanes ................................................................. 51951 and either 52109 or 53081. 


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5974 Federal Register / Vol. 71, No. 24 / Monday, February 6, 2006 / Rules and Regulations 

Unsafe Condition 

(d) This AD was prompted by reports of 

detached and damaged float valves in the left 

and right fuel tanks of the trimmable 

horizontal stabilizers (trim tanks). We are 

issuing this AD to prevent, in the event of a 

lightning strike to the horizontal stabilizer, 

sparking of metal parts and debris from 

detached and damaged float valves, or a 

buildup of static electricity, which could 

result in ignition of fuel vapors and 

consequent fire or explosion. 

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. 

Borescope Inspection 

(f) At the later of the times specified in 

paragraph (f)(1) and (f)(2) of this AD: Do a 

borescope inspection for detached or 

damaged float valves in the left and right trim 

tanks, by doing the applicable actions in the 

Accomplishment Instructions of Airbus 

Service Bulletins A330–28–3086, dated July 

24, 2003, and A330–28–3087, Revision 01, 

dated August 16, 2004 (for Model A330–201, 

–202, –203, –223, –243, –301, –321, –322, 

–323, –341, –342, and –343 airplanes); or 

A340–28–4100 and A340–28–4101, both 

Revision 01, both dated August 16, 2004 (for 

Model A340–211, –212, –213, –311, –312, 

and –313 airplanes); as applicable. 

(1) Prior to the accumulation of 2,500 total 

flight cycles or 15,000 total flight hours, 

whichever is first. 

(2) Within 7,500 flight hours after the 

effective date of this AD. 

Related Investigative and Corrective Actions 

(g) Depending on the results of the 

inspection required by paragraph (f) of this 

AD: Do the applicable actions in accordance 

with the Accomplishment Instructions of the 

applicable service bulletin identified in Table 

2 of this AD, at the times specified in Table 

2. 

TABLE 2.—INSPECTION RESULTS AND RELATED INVESTIGATIVE/CORRECTIVE ACTIONS

If inspection results 

reveal— Then— In accordance with Airbus service bulletin—

Detached or damaged 

float valve in the right 

trim tank.

Before further flight: (1) Remove the detached float and float debris from trim tank and do a 

detailed tank inspection for structural damage to the affected trim tank. Repair any structural damage to the trim tank or deactivate the trim tank, before further flight, in accordance with the applicable service bulletin, or in accordance with a method approved by 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). Where the service 

bulletin specifies to contact the manufacturer, instead contact the Manager, International 

Branch, ANM–116, or the DGAC (or its delegated agent)..

A330–28–3086, dated 

July 24, 2003. 

A340–28–4100, Revision 01, dated August 16, 2004. 

Before further flight, after doing the detailed inspection and repairing any structural damage: 

(2) Replace the affected float valve with a new unit having the same part number (P/N), or 

a new, improved float valve, P/N 62015–1, in accordance with the applicable service bulletin. If a new unit of P/N 61600 is installed, thereafter, do the inspection required by paragraph (f) of this AD at intervals not to exceed 2,500 flight cycles or 15,000 flight hours, 

whichever is first, after the most recent inspection, until paragraph (h) of this AD is accomplished..

A330–28–3086, dated 

July 24, 2003. 

A330–28–3088, dated 

April 27, 2004. 

A340–28–4100, Revision 01, dated August 16, 2004. 

A340–28–4102, dated 

April 27, 2004. 

Detached or damaged 

float valve in the left 

trim tank.

Before further flight: (1) Remove the detached float and float debris from the trim tank and 

do a detailed inspection for structural damage to the affected trim tank. Repair any structural damage to the trim tank or deactivate the trim tank, before further flight, in accordance with the applicable service bulletin, or in accordance with a method approved by the 

Manager, International Branch, ANM–116, FAA, Transport Airplane Directorate; or the 

DGAC (or its delegated agent). Where the service bulletin specifies to contact the manufacturer, instead contact the Manager, International Branch, ANM–116, or the DGAC (or 

its delegated agent)..

A330–28–3087, Revision 01, dated August 16, 2004. 

A340–28–4101, Revision 01, dated August 16, 2004. 

Before further flight, after doing the detailed inspection and repairing any structural damage: 

(2) Replace the affected float valve with either a new unit having that same P/N, or a new 

improved float valve, P/N L87–13–002 or P/N L87–13–003. If a new unit of P/N L87–13–

001 is installed, thereafter, do the inspection required by paragraph (f) of this AD at intervals not to exceed 2,500 flight cycles or 15,000 flight hours, whichever is first, after the 

most recent inspection, until paragraph (h) of this AD is accomplished. For Airbus Model 

A330–201, –202, –203, –223, –243, –301, –321, –322, –323, –341, –342, and –343 airplanes: If a float valve having P/N L87–13–002 is installed, thereafter, replace that float 

valve with a float valve having that same P/N at intervals not to exceed those specified in 

paragraph (h) of this AD. Installation of P/N L87–13–003 on Airbus Model A330–201, 

–202, –203, –223, –243, –301, –321, –322, –323, –341, –342, and –343 airplanes terminates the repetitive float valve replacement required by paragraph (h) of this AD..

A330–28–3087, Revision 01, dated August 16, 2004. 

A330–28–3089, Revision 02, dated April 

1, 2005. 

A330–28–3093, dated 

June 16, 2005. 

A330–28–3094, dated 

April 7, 2005. 

A340–28–4101, Revision 01, dated August 16, 2004. 

A340–28–4103, Revision 02, dated April 

1, 2005. 

A340–28–4111, dated 

April 6, 2005. 

No damaged or detached float valve in 

the left trim tank.

Within 10,000 flight hours or 1,500 flight cycles, whichever is first, from the initial inspection 

done in accordance with paragraph (f) of this AD, replace the existing Argo-Tech float 

valve, P/N 61600, with either a new unit having that same P/N, or a new, improved float 

valve, P/N 62015–1. If a new unit of P/N 61600 is installed, thereafter, repeat the inspection required by paragraph (f) of this AD at intervals not to exceed 2,500 flight cycles or 

15,000 flight hours, whichever is first, until paragraph (h) of this AD is accomplished..

A330–28–3086, dated 

July 24, 2003. 

A330–28–3088, dated 

April 27, 2004. 

A340–28–4100, Revision 01, dated August 16, 2004. 

A340–28–4102, dated 

April 27, 2004. 


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TABLE 2.—INSPECTION RESULTS AND RELATED INVESTIGATIVE/CORRECTIVE ACTIONS—Continued 

If inspection results 

reveal— Then— In accordance with Airbus service bulletin—

No damaged or detached float valve in 

the left trim tank.

Within 10,000 flight hours or 1,500 flight cycles, whichever is first, from the initial inspection 

done in accordance with paragraph (f) of this AD, replace the existing Intertechnique float 

valve, P/N L87–13–001, with either a new unit having that same P/N, or a new improved 

float valve, P/N L87–13–002 or P/N L87–13–003. If a new unit of P/N L87–13–001 is installed, thereafter, do the inspection required by paragraph (f) of this AD at intervals not to 

exceed 2,500 flight cycles or 15,000 flight hours, whichever is first, after the most recent 

inspection, until paragraph (h) of this AD is accomplished. For Airbus Model A330–201, 

–202, –203, –223, –243, –301, –321, –322, –323, –341, –342, and –343 airplanes: If a 

float valve having P/N L87–13–002 is installed, thereafter, replace that float valve with a 

float valve having that same P/N at intervals not to exceed those specified in paragraph 

(h) of this AD. Installation of P/N L87–13–003 on Airbus Model A330–201, –202, –203, 

–223, –243, –301, –321, –322, –323, –341, –342, and –343 airplanes terminates the repetitive float valve replacement required by paragraph (h) of this AD..

A330–28–3087, Revision 01, dated August 16, 2004. 

A330–28–3089, Revision 02, dated April 

1, 2005. 

A330–28–3093, dated 

June 16, 2005. 

A330–28–3094, dated 

April 7, 2005. 

A340–28–4101, Revision 01, dated August 16, 2004. 

A340–28–4103, Revision 02, dated April 

1, 2005. 

A340–28–4111, dated 

April 6, 2005. 

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.’’

Installation of New, Improved Float Valves 

(h) Within 50 months after the effective 

date of this AD: Replace any Argo-Tech float 

valve, P/N 61600, with a new, improved float 

valve, P/N 62015–1; replace any 

Intertechnique float valve, P/N L87–13–001, 

with a new, improved float valve, P/N L87–

13–002 or P/N L87–13–003; and do any 

applicable corrective action; by 

accomplishing the actions specified in the 

Accomplishments Instructions of the 

applicable service bulletin in Table 3 of this 

AD. Do any applicable corrective action 

before further flight. For Airbus Model A330–

201, –202, –203, –223, —243, –301, –321, 

–322, –323, –341, –342, and –343 airplanes: 

If P/N L87–13–002 is installed, replace the 

float valve thereafter at intervals not to 

exceed 24,500 flight cycles. Installation of P/ 

N L87–13–003 on Airbus Model A330–201, 

–202, –203, –223, —243, –301, –321, –322, 

–323, –341, –342, and –343 airplanes 

terminates the repetitive float valve 

replacement required by this paragraph. 

Installation of either P/N L87–13–002 or P/ 

N L87–13–003 terminates the borescope 

inspections required by paragraphs (f) and (g) 

of this AD. Where the service bulletin 

specifies to contact the manufacturer, instead 

contact the Manager, International Branch, 

ANM–116, or the DGAC (or its delegated 

agent). 

TABLE 3.—SERVICE INFORMATION FOR NEW FLOAT VALVES

Airbus model Float valve 

P/N Airbus service bulletin 

A330–201, –202, –203, 

–223, —243, –301, 

–321, –322, –323, –341, 

–342, and –343 airplanes.

62015–1 ..

L87–13–

002.

L87–13–

003.

L87–13–

003.

A330–28–3088, dated April 27, 2004. 

A330–28–3089, Revision 02, dated April 1, 2005. 

A330–28–3093, dated June 16, 2005. 

A330–28–3094, dated April 7, 2005. 

A340–211, –212, –213, 

–311, –312, and —313 

airplanes.

62015–1 ..

L87–13–

002.

L87–13–

003.

A340–28–4102, dated April 27, 2004. 

A340–28–4103, Revision 02, dated April 1, 2005. 

A340–28–4111, dated April 6, 2005. 

A340–541— and –642 airplanes.62015–1 ..

L87–13–

002.

L87–13–

003.

A340–28–5007, dated May 7, 2004. 

A340–28–5010, dated may 7, 2004. 

A340–28–5021, dated April 6, 2005. 

Actions Accomplished Previously 

(i) Inspections and related investigative 

and corrective actions accomplished before 

the effective date of this AD, in accordance 

with any applicable Airbus service bulletin 

identified in Table 4 of this AD, are 

acceptable for compliance with the 

corresponding actions specified in this AD. 


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5976 Federal Register / Vol. 71, No. 24 / Monday, February 6, 2006 / Rules and Regulations 

TABLE 4.—SERVICE INFORMATION FOR ACTIONS ACCOMPLISHED PREVIOUSLY

Airbus model Airbus service bulletin 

A330–201, –202, –203, –223, —243, –301, 

–321, –322, –323, –341, –342, and –343 airplanes.

A330–28–3087, dated July 24, 2003. 

A330–28–3089, Revision 01, dated May 12, 2004. 

A340–211, –212, –213, –311, –312, and —313 

airplanes.

A340–28–4100, dated July 24, 2003. 

A340–28–4101, dated July 24, 2003. 

A340–28–4103, Revision 01, dated May 12, 2004. 

A340–28–5010, dated May 7, 2004. 

A340–28–5021, dated April 6, 2005. 

No Submission of Information/Parts 

(j) Where any Airbus service bulletin 

specifies to submit information to Airbus, or 

send removed float valves to either ArgoTech or Intertechnique, those actions are not 

required by this AD. 

Alternative Methods of Compliance 

(AMOCs) 

(k)(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 

(l) French airworthiness directives F–

2005–003, dated January 5, 2005, and F–

2005–004 R1 and F–2005–005 R1, both dated 

April 27, 2005, also address the subject of 

this AD. 

Material Incorporated by Reference 

(m) You must use the documents specified 

in Table 5 of this AD 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 Airbus, 1 Rond Point 

Maurice Bellonte, 31707 Blagnac Cedex, 

France, 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. 

TABLE 5.—MATERIAL INCORPORATED BY REFERENCE

Airbus service bulletin Revision 

level Date 

A330–28–3086, excluding Appendix 01 ........................................................................... Original .... July 24, 2003. 

A330–28–3087, excluding Appendix 01 ........................................................................... 01 ............. August 16, 2004. 

A330–28–3088 ................................................................................................................. Original .... April 27, 2004. 

A330–28–3089 ................................................................................................................. 02 ............ April 1, 2005. 

A330–28–3093 ................................................................................................................. Original .... June 16, 2005. 

A330–28–3094 ................................................................................................................. Original .... April 7, 2005. 

A340–28–4100 ................................................................................................................. 01 ............ August 16, 2004. 

A340–28–4101, excluding Appendix 01 ........................................................................... 01 ............. August 16, 2004. 

A340–28–4102 ................................................................................................................. Original .... April 27, 2004. 

A340–28–4103 ................................................................................................................. 02 ............ April 1, 2005. 

A340–28–4111 ................................................................................................................. Original .... April 6, 2005. 

A340–28–5007 ................................................................................................................. Original .... May 7, 2004. 

A340–28–5010 ................................................................................................................. Original .... May 7, 2004. 

A340–28–5021 ................................................................................................................. Original .... April 6, 2005. 

Issued in Renton, Washington, on January 

27, 2006. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 06–989 Filed 2–3–06; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. 2003–NM–271–AD; Amendment 

39–14470; AD 2006–03–06] 

RIN 2120–AA64 

Airworthiness Directives; Empresa 

Brasileira de Aeronautica S.A. 

(EMBRAER) Model EMB–135 Airplanes 

and Model EMB–145, –145ER, –145MR, 

–145LR, –145XR, –145MP, and –145EP 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: This amendment adopts a 

new airworthiness directive (AD), 

applicable to all Empresa Brasileira de 

Aeronautica S.A. (EMBRAER) Model 

EMB–135 airplanes, and EMB–145, 

–145ER, –145MR, –145LR, –145XR, 

–145MP, and –145EP airplanes. This AD 

requires inspecting the pilot’s and copilot’s seat tracks for proper locking of 

the seats, and adjusting or replacing the 

seat tracks if necessary. This AD also 

requires replacement of the seat locking 

pin on certain SICMA-brand seats. The 

actions specified by this AD are 

intended to prevent uncommanded 

movement of the pilot’s or co-pilot’s 

seat, which could interfere with the 


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