Federal Register / Vol. 74, No. 173 / Wednesday, September 9, 2009 / Rules and Regulations 46319 

Related Information 

(h) Refer to MCAI Canadian Airworthiness 

Directive CF–2009–01, dated January 19, 

2009; Bombardier Dash 8 Q400 TA 14, Issue 

1, dated May 10, 2006; and Bombardier 

Service Bulletin 84–61–03, Revision ‘A,’ 

dated September 18, 2008; for related 

information. 

Material Incorporated by Reference 

(i) You must use Bombardier Dash 8 Q400 

Temporary Amendment 14, Issue 1, dated 

May 10, 2006; and Bombardier Service 

Bulletin 84–61–03, Revision ‘A,’ dated 

September 18, 2008; 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 Bombardier, Inc., 400 CoˆteVertu Road West, Dorval, Que ́bec H4S 1Y9, 

Canada; telephone 514–855–5000; fax 514– 

855–7401; e-mail 

thd.qseries@aero.bombardier.com; Internet 

http://www.bombardier.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 August 

18, 2009. 

Stephen P. Boyd, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. E9–20836 Filed 9–8–09; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2009–0563; Directorate 

Identifier 2008–NM–180–AD; Amendment 

39–16005; AD 2009–18–09] 

RIN 2120–AA64 

Airworthiness Directives; Fokker 

Model F.28 Mark 0070 and 0100 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: We are superseding an 

existing airworthiness directive (AD) for 

the products listed above. This AD 

results from mandatory continuing 

airworthiness information (MCAI) 

originated by an aviation authority of 

another country to identify and correct 

an unsafe condition on an aviation 

product. The MCAI describes the unsafe 

condition as: 

A recent design review has been carried 

out on the F28 Mark 0070/0100 fuel system 

in accordance with the guidelines related to 

FAA SFAR 88 [Special Federal Aviation 

Regulation No. 88] (Fuel Tank Safety 

Program) and JAA [Joint Aviation 

Authorities] INT/POL/25/12. The review 

revealed that under certain failure 

conditions, prolonged dry running of the fuel 

transfer pumps may result in an ignition 

source in the centre wing fuel tank. This 

condition, if not corrected, could lead to 

ignition of flammable fuel vapors, resulting 

in fuel tank explosion and consequent loss of 

the aircraft. 

* * * * * 

We are issuing this AD to require 

actions to correct the unsafe condition 

on these products. 

DATES: This AD becomes effective 

October 14, 2009. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in this AD 

as of October 14, 2009. 

On October 27, 1999 (64 FR 51202, 

September 22, 1999), the Director of the 

Federal Register approved the 

incorporation by reference of certain 

other publications listed in this AD. 

ADDRESSES: You may examine the AD 

docket on the Internet at http:// 

www.regulations.gov or in person at the 

U.S. Department of Transportation, 

Docket Operations, M–30, West 

Building Ground Floor, Room W12–140, 

1200 New Jersey Avenue, SE., 

Washington, DC. 

FOR FURTHER INFORMATION CONTACT: Tom 

Rodriguez, Aerospace Engineer, 

International Branch, ANM–116, 

Transport Airplane Directorate, FAA, 

1601 Lind Avenue, SW., Renton, 

Washington 98057–3356; telephone 

(425) 227–1137; fax (425) 227–1149. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to include an AD that would 

apply to the specified products. That 

NPRM was published in the Federal 

Register on June 19, 2009 (74 FR 29144), 

and proposed to supersede AD 99–20– 

01, Amendment 39–11329 (64 FR 

51202, September 22, 1999). That NPRM 

proposed to correct an unsafe condition 

for the specified products. The MCAI 

states: 

A recent design review has been carried 

out on the F28 Mark 0070/0100 fuel system 

in accordance with the guidelines related to 

FAA SFAR 88 [Special Federal Aviation 

Regulation No. 88] (Fuel Tank Safety 

Program) and JAA [Joint Aviation 

Authorities] INT/POL/25/12. The review 

revealed that under certain failure 

conditions, prolonged dry running of the fuel 

transfer pumps may result in an ignition 

source in the centre wing fuel tank. This 

condition, if not corrected, could lead to 

ignition of flammable fuel vapors, resulting 

in fuel tank explosion and consequent loss of 

the aircraft. 

To address and correct this unsafe 

condition, new software (version V13.55) has 

been developed for the Flight Warning 

Computer (FWC). This software update 

introduces a decreased time delay of the 

centre wing fuel tank low pressure alert from 

15 minutes to 60 seconds, to stop prolonged 

dry running of the fuel transfer pumps. 

For the reasons described above, this EASA 

Airworthiness Directive (AD) requires the 

replacement of the FWC with a modified 

unit, incorporating software version V13.55. 

The corrective actions include 

revising the airplane flight manual 

(AFM) to change certain indications and 

warnings; installing new software for 

the multifunction display unit (MFDU); 

and installing a new resistor in the 

thrust reverser indicator and control 

system, or an improved thrust reverser 

unlock indication relay. You may obtain 

further information by examining the 

MCAI in the AD docket. 

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. 

Conclusion 

We reviewed the available data and 

determined that air safety and the 

public interest require adopting the AD 

as proposed. 

Differences Between This AD and the 

MCAI or Service Information 

We have reviewed the MCAI and 

related service information and, in 

general, agree with their substance. But 

we might have found it necessary to use 

different words from those in the MCAI 

to ensure the AD is clear for U.S. 

operators and is enforceable. In making 

these changes, we do not intend to differ 

substantively from the information 

provided in the MCAI and related 

service information. 

We might also have required different 

actions in this AD from those in the 

MCAI in order to follow our FAA 

policies. Any such differences are 

highlighted in a note within the AD. 


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Costs of Compliance 

We estimate that this AD affects about 

4 products of U.S. registry. 

The actions that are required by AD 

99–20–01 and retained in this AD take 

about 7 work-hours per product, at an 

average labor rate of $80 per work hour. 

Required parts cost about $1,593 per 

product. Based on these figures, the 

estimated cost of the currently required 

actions is $2,153 per product. 

We estimate that it takes about 7 

work-hours per product to comply with 

the new basic requirements of this AD. 

The average labor rate is $80 per workhour. Required parts cost about $5,350 

per product. Where the service 

information lists required parts costs 

that are covered under warranty, we 

have assumed that there will be no 

charge for these costs. As we do not 

control warranty coverage for affected 

parties, some parties may incur costs 

higher than estimated here. Based on 

these figures, we estimate the cost of 

this AD to U.S. operators to be $23,640, 

or $5,910 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 

We 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 this AD: 

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 AD and placed it in the AD docket. 

Examining the AD Docket 

You may examine the AD docket on 

the Internet at http:// 

www.regulations.gov; or in person at the 

Docket Operations office between 9 a.m. 

and 5 p.m., Monday through Friday, 

except Federal holidays. The AD docket 

contains the NPRM, the regulatory 

evaluation, any comments received, and 

other information. The street address for 

the Docket Operations office (telephone 

(800) 647–5527) is in the ADDRESSES

section. Comments will be available in 

the AD docket shortly after receipt. 

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 

removing Amendment 39–11329 (64 FR 

51202, September 22, 1999) and adding 

the following new AD: 

2009–18–09 Fokker Services B.V.: 

Amendment 39–16005. Docket No. 

FAA–2009–0563; Directorate Identifier 

2008–NM–180–AD. 

Effective Date 

(a) This airworthiness directive (AD) 

becomes effective October 14, 2009. 

Affected ADs 

(b) This AD supersedes AD 99–20–01, 

Amendment 39–11329. 

Applicability 

(c) This AD applies to airplanes, 

certificated in any category, as identified in 

paragraphs (c)(1) and (c)(2) of this AD. 

(1) Fokker Model F.28 Mark 0100 

airplanes, all serial numbers. 

(2) Fokker Model F.28 Mark 0070 

airplanes, serial numbers 11521, 11528 

through 11537 inclusive, 11545, 11547, 

11553, 11557, 11561, 11562, 11566, 11567, 

11571, 11572, 11576 through 11579 

inclusive, and 11581 through 11583 

inclusive. All airplanes with these serial 

numbers are fitted with center wing fuel 

tanks. 

Subject 

(d) Air Transport Association (ATA) of 

America Codes 31 and 78: Instruments and 

Engine Exhaust, respectively. 

Reason 

(e) The mandatory continuing 

airworthiness information (MCAI) states: 

A recent design review has been carried 

out on the F28 Mark 0070/0100 fuel system 

in accordance with the guidelines related to 

FAA SFAR 88 [Special Federal Aviation 

Regulation No. 88] (Fuel Tank Safety 

Program) and JAA [Joint Aviation 

Authorities] INT/POL/25/12. The review 

revealed that under certain failure 

conditions, prolonged dry running of the fuel 

transfer pumps may result in an ignition 

source in the centre wing fuel tank. This 

condition, if not corrected, could lead to 

ignition of flammable fuel vapors, resulting 

in fuel tank explosion and consequent loss of 

the aircraft. 

To address and correct this unsafe 

condition, new software (version V13.55) has 

been developed for the Flight Warning 

Computer (FWC). This software update 

introduces a decreased time delay of the 

centre wing fuel tank low pressure alert from 

15 minutes to 60 seconds, to stop prolonged 

dry running of the fuel transfer pumps. 

For the reasons described above, this EASA 

Airworthiness Directive (AD) requires the 

replacement of the FWC with a modified 

unit, incorporating software version V13.55. 

The corrective actions include revising the 

airplane flight manual (AFM) to change 

certain indications and warnings; installing 

new software for the multifunction display 

unit (MFDU); and installing a new resistor in 

the thrust reverser indicator and control 

system, or an improved thrust reverser 

unlock indication relay. 

Restatement of Requirements of AD 99–20– 

01 With No Changes to the Modifications 

(f) Unless already done, within 18 months 

after October 27, 1999 (the effective date of 

AD 99–20–01), modify the electrical wiring 

of the FWC in accordance with Part 1 or 2, 

as applicable, of the Accomplishment 

Instructions of Fokker Service Bulletin 

SBF100–31–047, Revision 1, dated March 21, 

1997. 

Note 1: It is not necessary to install 

computer software version V10.40 into the 

FWC, since a later version is available and is 

required to be installed by AD 99–20–01. 

(g) Unless already done, concurrently with 

the accomplishment of the requirements of 

paragraph (f) of this AD, install upgraded 

computer software version V11.45 into the 

FWC in accordance with Fokker Service 

Bulletin SBF100–31–051, dated August 15, 

1998. 

Note 2: AlliedSignal Grimes Aerospace has 

issued Service Bulletin 80–0610–31–0031, 

dated May 14, 1998, as an additional source 


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of guidance for installation of the upgraded 

computer software version into the FWC. 

Note 3: Operators should note that Fokker 

Service Bulletin SBF100–31–051, dated 

August 15, 1998, specifies prior or 

concurrent accomplishment of Fokker 

Service Bulletin SBF100–78–014 (which 

specifies concurrent accomplishment of 

Fokker Component Service Bulletin (CSB) 

P41440–78–04, and prior or concurrent 

accomplishment of Fokker Service Bulletin 

SBF100–78–012 and CSB P41440–78–05). 

Related FAA AD 99–20–02, amendment 39– 

11330, requires accomplishment of these four 

other service bulletins. 

New Requirements of This AD: Actions and 

Compliance 

(h) Unless already done, do the following 

actions. 

(1) Within 36 months after the effective 

date of this AD, replace FWC units having 

part number (P/N) 80–0610–3–45 and P/N 

80–0610–3–50 with modified units having 

P/N 80–0610–3–55, in accordance with the 

Accomplishment Instructions of Fokker 

Service Bulletin SBF100–31–067, Revision 1, 

dated April 24, 2008. 

(2) Within 36 months after the effective 

date of this AD and concurrently with the 

accomplishment of paragraph (h)(1) of this 

AD, revise the Emergency and Abnormal 

Procedures sections of the airplane flight 

manual (AFM), as specified in Fokker 

Manual Change Notification-Operational 

Documentation MCNO–F100–050, dated 

January 31, 2008, which is included in 

Fokker Service Bulletin SBF100–31–067, 

Revision 1, dated April 24, 2008. These AFM 

sections provide alterations, which are 

introduced in Fokker Service Bulletin 

SBF100–31–067, Revision 1, dated April 24, 

2008. 

Note 4: Revisions to the Emergency 

Procedures and Abnormal Procedures 

sections of the AFM, as specified in Fokker 

MCNO–F100–050, dated January 31, 2008, 

may be done by inserting copies of Fokker 

MCNO–F100–050, dated January 31, 2008, 

into the AFM. When the information in 

Fokker MCNO–F100–050, dated January 31, 

2008, has been included in general revisions 

of the AFM, the general revisions may be 

inserted in the AFM, provided the relevant 

information in the general revisions are 

identical to that in Fokker MCNO–F100–050, 

dated January 31, 2008. 

(3) After accomplishing paragraph (h)(1) of 

this AD, no person may install an FWC 

having P/N 80–0610–3–45 or P/N 80–0610– 

3–50, unless it has been modified to P/N 80– 

0610–3–55 standard in accordance with 

Honeywell Service Bulletin 80–0610–31– 

0003, dated February 13, 2008. 

(4) Within 36 months after the effective 

date of this AD, install software version V12 

for the MFDU in accordance with the 

Accomplishment Instructions of Fokker 

Service Bulletin SBF100–31–060, dated June 

1, 2002. 

(5) Within 36 months after the effective 

date of this AD, modify the thrust reverser 

indication and control system in accordance 

with the Accomplishment Instructions of 

Fokker Service Bulletin SBF100–78–016, 

dated October 1, 1999; or modify the thrust 

reverser unlock indication relay in 

accordance with the Accomplishment 

Instructions of Fokker Service Bulletin 

SBF100–78–017, dated December 1, 1999. 

FAA AD Differences 

Note 5: This AD differs from the MCAI 

and/or service information as follows: 

(1) Replacing the MFDU in accordance 

with Fokker Service Bulletin SBF100–31– 

060, dated June 1, 2002, is not included in 

the MCAI; however, this AD includes that 

action. It is necessary to install a new version 

of the MFDU software before installing the 

new version of the FWC software. 

(2) Modifying the thrust reverser indication 

and control system in accordance with 

Fokker Service Bulletin SBF100–78–016, 

dated October 1, 1999; or modifying the 

thrust reverser unlock indication relay in 

accordance with Fokker Service Bulletin 

SBF100–78–017, dated December 1, 1999, is 

not included in the MCAI; however, this AD 

includes those actions. It is necessary to do 

one of those actions before installing the 

MFDU software. 

Other FAA AD Provisions 

(i) 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: Tom Rodriguez, 

Aerospace Engineer, International Branch, 

ANM–116, Transport Airplane Directorate, 

FAA, 1601 Lind Avenue, SW., Renton, 

Washington 98057–3356; telephone (425) 

227–1137; fax (425) 227–1149. 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. 

(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. 

(3) Reporting Requirements: For any 

reporting requirement in this AD, under the 

provisions of the Paperwork Reduction Act, 

the Office of Management and Budget (OMB) 

has approved the information collection 

requirements and has assigned OMB Control 

Number 2120–0056. 

Related Information 

(j) Refer to MCAI European Aviation Safety 

Agency Airworthiness Directive 2008–0090, 

dated May 13, 2008, and the service 

information identified in Table 1 of this AD, 

for related information. 

TABLE 1—RELATED INFORMATION

Service information— Revision level— Dated— 

Fokker Service Bulletin SBF100–31–047 .......................... 1 ......................................................................................... March 21, 1997. 

Fokker Service Bulletin SBF100–31–051 .......................... Original ............................................................................... August 15, 1998. 

Fokker Service Bulletin SBF100–31–060 .......................... Original ............................................................................... June 1, 2002. 

Fokker Service Bulletin SBF100–31–067, including 

Fokker Manual Change Notification-Operational Documentation MCNO–F100–50, dated January 31, 2008.

1 ......................................................................................... April 24, 2008. 

Fokker Service Bulletin SBF100–78–016 .......................... Original ............................................................................... October 1, 1999. 

Fokker Service Bulletin SBF100–78–017 .......................... Original ............................................................................... December 1, 1999. 

Material Incorporated by Reference 

(k) You must use the service information 

contained in Table 2 of this AD to do the 

actions required by this AD, unless the AD 

specifies otherwise. 

TABLE 2—ALL MATERIAL INCORPORATED BY REFERENCE

Document Revision Date 

Fokker Service Bulletin SBF100–31–047 .......................... 1 ......................................................................................... March 21, 1997. 

Fokker Service Bulletin SBF100–31–051 .......................... Original ............................................................................... August 15, 1998. 


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46322 Federal Register / Vol. 74, No. 173 / Wednesday, September 9, 2009 / Rules and Regulations 

TABLE 2—ALL MATERIAL INCORPORATED BY REFERENCE—Continued 

Document Revision Date 

Fokker Service Bulletin SBF100–31–060 .......................... Original ............................................................................... June 1, 2002. 

Fokker Service Bulletin SBF100–31–067, including 

Fokker Manual Change Notification-Operational Documentation MCNO–F100–50, dated January 31, 2008.

1 ......................................................................................... April 24, 2008. 

Fokker Service Bulletin SBF100–78–016 .......................... Original ............................................................................... October 1, 1999. 

Fokker Service Bulletin SBF100–78–017 .......................... Original ............................................................................... December 1, 1999. 

(1) The Director of the Federal Register 

approved the incorporation by reference of 

the service information contained in Table 3 

of this AD under 5 U.S.C. 552(a) and 1 CFR 

part 51. 

TABLE 3—NEW MATERIAL INCORPORATED BY REFERENCE

Document Revision Date 

Fokker Service Bulletin SBF100–31–060 .......................... Original ............................................................................... June 1, 2002. 

Fokker Service Bulletin SBF100–31–067, including 

Fokker Manual Change Notification-Operational Documentation MCNO–F100–50, dated January 31, 2008.

1 ......................................................................................... April 24, 2008. 

Fokker Service Bulletin SBF100–78–016 .......................... Original ............................................................................... October 1, 1999. 

Fokker Service Bulletin SBF100–78–017 .......................... Original ............................................................................... December 1, 1999. 

(2) The Director of the Federal Register 

previously approved the incorporation by 

reference of Fokker Service Bulletin SBF100– 

31–047, Revision 1, dated March 21, 1997; 

and Fokker Service Bulletin SBF100–31–051, 

dated August 15, 1998; on October 27, 1999 

(64 FR 51202, September 22, 1999). 

(3) For Fokker service information 

identified in this AD, contact Fokker Services 

B.V., Technical Services Dept., P.O. Box 231, 

2150 AE Nieuw-Vennep, the Netherlands; 

telephone +31 (0)252–627–350; fax +31 

(0)252–627–211; e-mail 

technicalservices.fokkerservices@stork.com; 

Internet http://www.myfokkerfleet.com. 

(4) For AlliedSignal Grimes Aerospace and 

Honeywell service information identified in 

this AD, contact Honeywell Aerospace, 

Technical Publications and Distribution, 

M/S 2101–201, P.O. Box 52170, Phoenix, 

Arizona 85072–2170; telephone 602–365– 

5535; fax 602–365–5577; Internet http:// 

www.honeywell.com. 

(5) 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. 

(6) 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 August 

18, 2009. 

Stephen P. Boyd, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. E9–20840 Filed 9–8–09; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2009–0381; Directorate 

Identifier 2009–NM–008–AD; Amendment 

39–16016; AD 2009–18–19] 

RIN 2120–AA64 

Airworthiness Directives; Airbus Model 

A330–200 and –300 Series Airplanes 

and Model A340–200 and –300 Series 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for the 

products listed above. This AD results 

from mandatory continuing 

airworthiness information (MCAI) 

originated by an aviation authority of 

another country to identify and correct 

an unsafe condition on an aviation 

product. The MCAI describes the unsafe 

condition as: 

An A340 operator has reported an 

uncommanded engine N°4 shut down during 

taxi after landing. 

The root cause of this event has been 

identified as failure of the fuel pump Non 

Return Valve (NRV) preventing the collector 

cell jet pump from working. This led to 

engine N°4 collector cell fuel level to drop 

below the pump inlet and consequently 

causing engine N°4 flame out. 

* * * * * 

Multiple NRV failures in combination with 

failure modes trapping fuel could potentially 

increase the quantity of unusable fuel on 

aircraft possibly leading to fuel starvation 

which could result in engine in-flight shut 

down and would constitute an unsafe 

condition. 

* * * * * 

We are issuing this AD to require 

actions to correct the unsafe condition 

on these products. 

DATES: This AD becomes effective 

October 14, 2009. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in this AD 

as of October 14, 2009. 

ADDRESSES: You may examine the AD 

docket on the Internet at http:// 

www.regulations.gov or in person at the 

U.S. Department of Transportation, 

Docket Operations, M–30, West 

Building Ground Floor, Room W12–140, 

1200 New Jersey Avenue, SE., 

Washington, DC. 

FOR FURTHER INFORMATION CONTACT: 

Vladimir Ulyanov, Aerospace Engineer, 

International Branch, ANM–116, 

Transport Airplane Directorate, FAA, 

1601 Lind Avenue, SW., Renton, 

Washington 98057–3356; telephone 

(425) 227–1138; fax (425) 227–1149. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to include an AD that would 

apply to the specified products. That 

NPRM was published in the Federal 

Register on April 29, 2009 (74 FR 

19464). That NPRM proposed to correct 


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