55116 Federal Register / Vol. 74, No. 206 / Tuesday, October 27, 2009 / Rules and Regulations 

hydraulic circuits at the same time. This will 

mitigate the risk of having a malfunction on 

the three hydraulic systems at the same time. 

FAA AD Differences 

Note 3: This AD differs from the MCAI 

and/or service information as follows: 

This AD does not include the reporting 

requirement specified in paragraph (1) of the 

MCAI. The MCAI carried this requirement 

forward from European Aviation Safety 

Agency (EASA) Airworthiness Directive 

2007–0245, dated September 5, 2007. We 

previously determined that no action was 

required on our part regarding EASA AD 

2007–0245. 

Other FAA AD Provisions 

(g) The following provisions also apply to 

this AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, International 

Branch, ANM–116, Transport Airplane 

Directorate, FAA, has the authority to 

approve AMOCs for this AD, if requested 

using the procedures found in 14 CFR 39.19. 

Send information to ATTN: Dan Rodina, 

Aerospace Engineer, International Branch, 

ANM–116, Transport Airplane Directorate, 

FAA, 1601 Lind Avenue, SW., Renton, 

Washington 98057–3356; telephone (425) 

227–2125; fax (425) 227–1149. Before using 

any approved AMOC on any airplane to 

which the AMOC applies, notify your 

appropriate principal inspector (PI) in the 

FAA Flight Standards District Office (FSDO), 

or lacking a PI, your local FSDO. 

(2) Airworthy Product: For any requirement 

in this AD to obtain corrective actions from 

a manufacturer or other source, use these 

actions if they are FAA-approved. Corrective 

actions are considered FAA-approved if they 

are approved by the State of Design Authority 

(or their delegated agent). You are required 

to assure the product is airworthy before it 

is returned to service. 

Related Information 

(h) Refer to MCAI EASA Airworthiness 

Directive 2008–0058, dated March 20, 2008; 

and Airbus Mandatory Service Bulletin 

A300–27–6060, dated February 18, 2008; and 

Airbus Mandatory Service Bulletin A300– 

27A6062, dated July 6, 2007; for related 

information. 

Material Incorporated by Reference 

(i) You must use Airbus Mandatory Service 

Bulletin A300–27–6060, excluding Appendix 

1, dated February 18, 2008; and Airbus 

Mandatory Service Bulletin A300–27A6062, 

excluding Appendix 1, dated July 6, 2007; as 

applicable; to do the actions required by this 

AD, unless the AD specifies otherwise. 

(1) The Director of the Federal Register 

approved the incorporation by reference of 

this service information under 5 U.S.C. 

552(a) and 1 CFR part 51. 

(2) For service information identified in 

this AD, contact Airbus SAS–EAW 

(Airworthiness Office), 1 Rond Point Maurice 

Bellonte, 31707 Blagnac Cedex, France; 

telephone +33 5 61 93 36 96; fax +33 5 61 

93 44 51; e-mail: account.airwortheas@airbus.com; Internet http:// 

www.airbus.com. 

(3) You may review copies of the service 

information at the FAA, Transport Airplane 

Directorate, 1601 Lind Avenue SW., Renton, 

Washington. For information on the 

availability of this material at the FAA, call 

425–227–1221 or 425–227–1152. 

(4) You may also review copies of the 

service information that is incorporated by 

reference 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. 

Issued in Renton, Washington, on October 

7, 2009. 

Jeffrey E. Duven, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. E9–24938 Filed 10–26–09; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2009–0324; Directorate 

Identifier 2008–NM–186–AD; Amendment 

39–16039; AD 2009–21–02] 

RIN 2120–AA64 

Airworthiness Directives; Airbus Model 

A300 B4–601, B4–603, B4–605R, B4– 

620, B4–622, B4–622R, F4–605R, F4– 

622R, and C4–605R Variant F Series 

Airplanes Equipped With Simmonds 

Precision Products, Inc., Fuel Quantity 

Indicating System Sensors and In-Tank 

Harnesses Installed in Accordance 

With Supplemental Type Certificate 

(STC) ST00092BO 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for certain 

Airbus model series airplanes listed 

above. This AD requires revising the 

Airworthiness Limitations Section of 

the Instructions for Continuing 

Airworthiness to incorporate new fuel 

system limitations for airplanes 

modified in accordance with 

Supplemental Type Certificate (STC) 

ST00092BO. This AD also requires a 

general visual inspection for tank unit 

separation and compensator separation 

of the center, inner, and outer fuel 

tanks, and trim fuel tanks of the tank 

units, and corrective actions if 

necessary. This AD results from fuel 

system reviews conducted by the 

manufacturer. We are issuing this AD to 

prevent a potential of ignition sources 

inside fuel tanks, which in combination 

with flammable fuel vapors, could result 

in a fuel tank fire or explosion and 

consequent loss of the airplane. 

DATES: This AD is effective December 1, 

2009. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in the AD 

as of December 1, 2009. 

ADDRESSES: For service information 

identified in this AD, contact Goodrich 

Corporation, Sensors and Integrated 

Systems (Formerly Fuel and Utility 

Systems), 100 Panton Road, Vergennes, 

Vermont 05491–1008; telephone 802– 

877–4476; e-mail sis.techpubsvt@goodrich.com; Internet http:// 

www.goodrich.com/TechPubs. 

Examining the AD Docket 

You may examine the AD docket on 

the Internet at http:// 

www.regulations.gov; or in person at the 

Docket Management Facility between 9 

a.m. and 5 p.m., Monday through 

Friday, except Federal holidays. The AD 

docket contains this AD, the regulatory 

evaluation, any comments received, and 

other information. The address for the 

Docket Office (telephone 800–647–5527) 

is the Document Management Facility, 

U.S. Department of Transportation, 

Docket Operations, M–30, West 

Building Ground Floor, Room W12–140, 

1200 New Jersey Avenue, SE., 

Washington, DC 20590. 

FOR FURTHER INFORMATION CONTACT: 

Marc Ronell, Aerospace Engineer, ANE– 

150, FAA, Boston Aircraft Certification 

Office, 12 New England Executive Park, 

Burlington, Massachusetts 01803; 

telephone (781) 238–7776; fax (781) 

238–7170. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to include an airworthiness 

directive (AD) that would apply to 

certain Airbus Model A300 B4–601, B4– 

603, B4–605R, B4–620, B4–622, B4– 

622R, F4–605R, F4–622R, and C4–605R 

Variant F series airplanes. That NPRM 

was published in the Federal Register 

on April 9, 2009 (74 FR 16152). That 

NPRM proposed to require revising the 

Airworthiness Limitations Section 

(ALS) of the Instructions for Continuing 

Airworthiness to incorporate new fuel 

system limitations for airplanes 

modified in accordance with 

Supplemental Type Certificate (STC) 

ST00092BO. That NPRM also proposed 

to require a general visual inspection for 

tank unit separation and compensator 

separation of the center, inner, and 

outer fuel tanks, and trim fuel tanks of 


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Federal Register / Vol. 74, No. 206 / Tuesday, October 27, 2009 / Rules and Regulations 55117 

the tank units, and corrective actions if 

necessary. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. We 

received no comments on the NPRM or 

on the determination of the cost to the 

public. 

Actions Since NPRM Was Issued 

Since we issued that NPRM, we have 

determined that it is necessary to clarify 

the AD’s intended effect on spare and 

on-airplane fuel tank system 

components, regarding the use of 

maintenance manuals and instructions 

for continued airworthiness. 

Section 91.403(c) of the Federal 

Aviation Regulations (14 CFR 91.403(c)) 

specifies the following: 

No person may operate an aircraft for 

which a manufacturer’s maintenance manual 

or instructions for continued airworthiness 

has been issued that contains an 

airworthiness limitation section unless the 

mandatory * * * procedures * * * have 

been complied with. 

Some operators have questioned 

whether existing components affected 

by the new CDCCLs must be reworked. 

We did not intend for the AD to 

retroactively require rework of 

components that had been maintained 

using acceptable methods before the 

effective date of the AD. Owners and 

operators of the affected airplanes 

therefore are not required to rework 

affected components identified as 

airworthy or installed on the affected 

airplanes before the required revisions 

of the ALS. But once the CDCCLs are 

incorporated into the ALS, future 

maintenance actions on components 

must be done in accordance with those 

CDCCLs. 

We have added Note 2 to this AD to 

clarify the intended effect of the AD on 

spare and on-airplane fuel tank system 

components. 

Revision to Paragraph (h) of This AD 

We removed a redundant reference to 

the service information, ‘‘in accordance 

with Section 2.2.3 of the Goodrich 

A300–600 Instructions for Continued 

Airworthiness, Document T3012–0005– 

0101, Revision B, dated June 12, 2008,’’ 

from paragraph (h) of this AD. 

Revision to the Product Identification 

Line 

We have revised the product 

identification line that precedes 

paragraph (a) of this AD to specify 

Airbus. For ADs that apply to STCs 

installed on only one type of airplane, 

we identify the name of the airplane 

manufacturer in the product 

identification line. 

Revision to Paragraph (l) of this AD 

We have revised paragraph (l) of this 

AD to include the phrase, ‘‘if done 

before the effective date of this AD.’’ 

This text was inadvertently omitted. It 

was our intention to provide credit for 

operators which have completed the 

inspections specified in paragraph (h) of 

this AD, before the effective date of this 

AD, using Goodrich Service Bulletin 

300723–0101–28–01, Revision 1, dated 

July 1, 2004. 

Conclusion 

We reviewed the relevant data, and 

determined that air safety and the 

public interest require adopting the AD 

with the changes described previously. 

We also determined that these changes 

will not increase the economic burden 

on any operator or increase the scope of 

the AD. 

Costs of Compliance 

We estimate that this AD affects 68 

airplanes of U.S. registry. We also 

estimate that it takes about 8 work-hours 

per product to comply with this AD. 

The average labor rate is $80 per workhour. Based on these figures, we 

estimate the cost of this AD to the U.S. 

operators to be $43,520, or $640 per 

product. 

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 

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. 

You can find our regulatory 

evaluation and the estimated costs of 

compliance in the AD Docket. 

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 FAA amends § 39.13 by adding 

the following new AD: 

2009–21–02 Airbus: Amendment 39–16039. 

Docket No. FAA–2009–0324; Directorate 

Identifier 2008–NM–186–AD. 

Effective Date 

(a) This airworthiness directive (AD) is 

effective December 1, 2009. 

Affected ADs 

(b) This AD affects AD 2004–05–05, 

Amendment 39–13499. 

Applicability 

(c) This AD applies to Airbus Model A300 

B4–601, B4–603, B4–605R, B4–620, B4–622, 

B4–622R, F4–605R, F4–622R, and C4–605R 

Variant F series airplanes, certificated in any 

category, equipped with Simmonds Precision 

Products, Inc., Fuel Quantity Indicating 

System sensors and in-tank harnesses 

installed in accordance with Supplemental 

Type Certificate (STC) ST00092BO. 

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), 


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55118 Federal Register / Vol. 74, No. 206 / Tuesday, October 27, 2009 / Rules and Regulations 

the operator must request approval for an 

alternative method of compliance according 

to paragraph (o) of this AD. The request 

should include a description of changes to 

the required inspections that will ensure the 

continued operational safety of the airplane. 

Subject 

(d) Air Transport Association (ATA) of 

America Code 28: Fuel. 

Unsafe Condition 

(e) This AD results from fuel system 

reviews conducted by the manufacturer. The 

Federal Aviation Administration is issuing 

this AD to reduce the potential of ignition 

sources inside fuel tanks, which in 

combination with flammable fuel vapors, 

could result in fuel tank fire or explosions 

and consequent loss of the airplane. 

Compliance 

(f) You are responsible for having the 

actions required by this AD performed within 

the compliance times specified, unless 

already done. 

Revision to the Airworthiness Limitations 

Section To Incorporate Inspections 

(g) Within 30 days after the effective date 

of this AD, revise the Airworthiness 

Limitations Section (ALS) of the Instructions 

for Continued Airworthiness to incorporate 

the inspections specified in Section 2.2.3 of 

the Goodrich A300–600 Instructions for 

Continued Airworthiness, Document T3012– 

0005–0101, Revision B, dated June 12, 2008. 

Inspection for Correct Separation 

(h) Within 6 months after the effective date 

of this AD, do a general visual inspection for 

tank unit separation and compensator 

separation of the center, inner, and outer fuel 

tanks, and trim fuel tanks of the tank units, 

in accordance with Section 2.2.3 of the 

Goodrich A300–600 Instructions for 

Continued Airworthiness, Document T3012– 

0005–0101, Revision B, dated June 12, 2008. 

If incorrect separation is found, before further 

flight, correct the separation in accordance 

with the Airplane Maintenance Manual for 

the corresponding inspection specified in 

Section 2.2.3 of the Goodrich A300–600 

Instructions for Continued Airworthiness, 

Document T3012–0005–0101, Revision B, 

dated June 12, 2008. A review of airplane 

maintenance records is acceptable in lieu of 

this inspection if the requirement of Table 6 

in Section 10.1 of the Goodrich A300–600 

Instructions for Continued Airworthiness, 

Document T3012–0005–0101, Revision B, 

dated June 12, 2008, can be conclusively 

determined to have been done from that 

review. 

Revision to the ALS To Incorporate CDCCLs 

(i) Within 30 days after the effective date 

of this AD, revise the ALS of the Instructions 

for Continued Airworthiness to incorporate 

the CDCCLs, as defined in Section 10.1 of the 

Goodrich A300–600 Instructions for 

Continued Airworthiness, 

Document T3012–0005–0101, Revision B, 

dated June 12, 2008. 

(j) Except as provided by paragraph (o) of 

this AD: After accomplishing the actions 

specified in paragraphs (g) and (i) of this AD, 

no alternative inspection, inspection 

intervals, or CDCCLs may be used. 

Note 2: Notwithstanding any other 

maintenance or operational requirements, 

components that have been identified as 

airworthy or installed on the affected 

airplanes before the revision of the 

Airworthiness Limitations Section of the 

Instructions for Continuing Airworthiness, as 

required by paragraph (i) of this AD, do not 

need to be reworked in accordance with the 

CDCCLs. However, once the Airworthiness 

Limitations Section of the Instructions for 

Continuing Airworthiness has been revised, 

future maintenance actions on these 

components must be done in accordance 

with the CDCCLs. 

Actions Done According to Previous Service 

Information 

(k) Inspections are acceptable for 

compliance with the requirements of 

paragraph (h) of this AD, if done before the 

effective date of this AD, in accordance with 

Goodrich Service Bulletin 300723–0101–28– 

01, dated April 15, 2004. 

(l) Inspections are also acceptable for 

compliance with the requirements of 

paragraph (h) of this AD, if done before the 

effective date of this AD, in accordance with 

Goodrich Service Bulletin 300723–0101–28– 

01, Revision 1, dated July 1, 2004. 

Acceptable Methods of Compliance for AD 

2004–05–05 

(m) Doing the inspections in Section 2.2.3 

of the Goodrich A300–600 Instructions for 

Continued Airworthiness, Document T3012– 

0005–0101, Revision B, dated June 12, 2008, 

is considered an acceptable method of 

compliance with paragraphs (b) and (c) of AD 

2004–05–05. 

(n) Doing the inspections in accordance 

with Goodrich Service Bulletin 300723– 

0101–28–01, Revision 1, dated July 1, 2004, 

is an acceptable method of compliance with 

paragraphs (b) and (c) of AD 2004–05–05. 

Alternative Methods of Compliance 

(AMOCs) 

(o)(1) The Manager, Boston Aircraft 

Certification Office (ACO), FAA, has the 

authority to approve AMOCs for this AD, if 

requested using the procedures found in 14 

CFR 39.19. Send information to ATTN: Marc 

Ronell, Aerospace Engineer, ANE–150, FAA, 

Boston ACO, 12 New England Executive 

Park, Burlington, Massachusetts 01803; 

telephone (781) 238–7776; fax (781) 238– 

7170. 

(2) To request a different method of 

compliance or a different compliance time 

for this AD, follow the procedures in 14 CFR 

39.19. Before using any approved AMOC on 

any airplane to which the AMOC applies, 

notify your principal maintenance inspector 

(PMI) or principal avionics inspector (PAI), 

as appropriate, or lacking a principal 

inspector, your local Flight Standards District 

Office. The AMOC approval letter must 

specifically reference this AD. 

Material Incorporated by Reference 

(p) You must use Goodrich A300–600 

Instructions for Continued Airworthiness, 

Document T3012–0005–0101, Revision B, 

dated June 12, 2008, to do the actions 

required by this AD, unless the AD specifies 

otherwise. (The List of Effective Pages section 

of this document does not include pages iii, 

6, 15, and 16 of this document. Those pages 

are also at Revision B, dated June 12, 2008.) 

(1) The Director of the Federal Register 

approved the incorporation by reference of 

this service information under 5 U.S.C. 

552(a) and 1 CFR part 51. 

(2) For service information identified in 

this AD, contact Goodrich Corporation, 

Sensors and Integrated Systems (Formerly 

Fuel and Utility Systems), 100 Panton Road, 

Vergennes, Vermont 05491–1008; telephone 

802–877–4476; e-mail sis.techpubsvt@goodrich.com; Internet http:// 

www.goodrich.com/TechPubs. 

(3) You may review copies of the service 

information at the FAA, Transport Airplane 

Directorate, 1601 Lind Avenue, SW., Renton, 

Washington. For information on the 

availability of this material at the FAA, call 

425–227–1221 or 425–227–1152. 

(4) You may also review copies of the 

service information that is incorporated by 

reference 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. 

Issued in Renton, Washington, on 

September 18, 2009. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. E9–24011 Filed 10–26–09; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2009–0997; Directorate 

Identifier 2009–NM–158–AD; Amendment 

39–16062; AD 2007–22–03 R1] 

RIN 2120–AA64 

Airworthiness Directives; Airbus Model 

A300 Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule; request for 

comments. 

SUMMARY: The FAA is revising an 

existing airworthiness directive (AD), 

which applies to all Airbus Model A300 

airplanes. That AD currently requires 

revising the Airworthiness Limitations 

Section of the Instructions for 

Continued Airworthiness to incorporate 

new limitations for fuel tank systems. 

This AD clarifies the intended effect of 

the AD on spare and on-airplane fuel 

tank system components. This AD 


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