Federal Register / Vol. 73, No. 239 / Thursday, December 11, 2008 / Rules and Regulations 75307 

February 21, 2008, except as provided by 

paragraph (i) of this AD. Do all applicable 

corrective actions before further flight. 

Repeat the applicable inspection at the 

applicable time specified in paragraph 1.E. of 

Boeing Alert Service Bulletin 747–57A2323, 

dated February 21, 2008. 

Modification of Fail Safe Links of Main 

Carriage 

(g) For Groups 1, 2, and 3 airplanes: Within 

24 months after the effective date of this AD, 

replace the fail-safe links, pins, and 

attachment hardware in accordance with Part 

2 of the Accomplishment Instructions of 

Boeing Alert Service Bulletin 747–57A2323, 

dated February 21, 2008. 

Exception to Compliance Times 

(h) Where Boeing Alert Service Bulletin 

747–57A2323, dated February 21, 2008, 

specifies counting the compliance time from 

‘‘* * * the date on this service bulletin,’’ this 

AD requires counting the compliance time 

from the effective date of this AD. 

Exception to Corrective Actions 

(i) If any fractured support fitting is found 

during any inspection required by this AD, 

and Boeing Alert Service Bulletin 747– 

57A2323, dated February 21, 2008, specifies 

to contact Boeing for appropriate action: 

Before further flight, repair using a method 

approved in accordance with the procedures 

specified in paragraph (j) of this AD. 

Alternative Methods of Compliance 

(AMOCs) 

(j)(1) The Manager, Seattle Aircraft 

Certification Office (ACO), FAA, ATTN: Gary 

Oltman, Aerospace Engineer, Airframe 

Branch, ANM–120S, 1601 Lind Avenue, SW., 

Renton, Washington 98057–3356; telephone 

(425) 917–6443; fax (425) 917–6590; has the 

authority to approve AMOCs for this AD, if 

requested using the procedures found in 14 

CFR 39.19. 

(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 appropriate principal inspector 

(PI) in the FAA Flight Standards District 

Office (FSDO), or lacking a PI, your local 

FSDO. 

(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, Seattle ACO, to 

make those findings. For a repair method to 

be approved, the repair must meet the 

certification basis of the airplane, and the 

approval must specifically refer to this AD. 

Material Incorporated by Reference 

(k) You must use Boeing Alert Service 

Bulletin 747–57A2323, dated February 21, 

2008; 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 Boeing Commercial 

Airplanes, Attention: Data & Services 

Management, P.O. Box 3707, MC 2H–65, 

Seattle, Washington 98124–2207; telephone 

206–544–5000, extension 1, fax 206–766– 

5680; e-mail me.boecom@boeing.com; 

Internet https://www.myboeingfleet.com. 

(3) You may review copies of the service 

information that is incorporated by reference 

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 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 

November 28, 2008. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. E8–29073 Filed 12–10–08; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2007–27739; Directorate 

Identifier 2006–NM–250–AD; Amendment 

39–15760; AD 2008–25–02] 

RIN 2120–AA64 

Airworthiness Directives; Airbus Model 

A330 Airplanes; and Model A340–200 

and –300 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: 

* * * * * 

The aim of * * * [Special Federal Aviation 

Regulation (SFAR) 88] is to require all 

holders of type certificates * * * to carry out 

a definition review against explosion 

hazards. 

The unsafe condition is the potential 

of ignition sources inside fuel tanks, 

which, in combination with flammable 

fuel vapors, could result in fuel tank 

explosions and consequent loss of the 

airplane. We are issuing this AD to 

require actions to correct the unsafe 

condition on these products. 

DATES: This AD becomes effective 

January 15, 2009. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in this AD 

as of January 15, 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: Tim 

Backman, Aerospace Engineer, 

International Branch, ANM–116, FAA, 

Transport Airplane Directorate, 1601 

Lind Avenue, SW., Renton, Washington 

98057–3356; telephone (425) 227–2797; 

fax (425) 227–1149. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a supplemental notice of 

proposed rulemaking (NPRM) to amend 

14 CFR part 39 to include an AD that 

would apply to the specified products. 

That supplemental NPRM was 

published in the Federal Register on 

June 17, 2008 (73 FR 34228). That 

supplemental NPRM proposed to 

correct an unsafe condition for the 

specified products. The MCAI states: 

[T]he FAA published SFAR 88 (Special 

Federal Aviation Regulation 88). 

By mail referenced 04/00/02/07/01–L296 

of March 4th, 2002 and 04/00/02/07/03–L024 

of February 3rd, 2003 the JAA (Joint Aviation 

Authorities) recommended to the National 

Aviation Authorities (NAA) the application 

of a similar regulation. 

The aim of this regulation is to require all 

holders of type certificates for passenger 

transport aircraft certified after January 1st, 

1958 with a capacity of 30 passengers or 

more, or a payload of 3,402 kg or more, to 

carry out a definition review against 

explosion hazards. 

Consequently, the following measures [are] 

rendered mandatory * * *: 

• [inspection and] replacement [if 

necessary] of the white P-clips by blue Pclips which are more fuel resistant remove 

the risks of fuel quantity indicator (FQI) and 

fuel level sensor system (FLSS) harnesses 

chafing against the metallic part of the P-clip, 

• Modification of electrical bonding of 

equipment installed in fuel tanks in order to 

re-establish the conformity with the design 

definition by introducing additional bonding 

leads, electrical bonding points and electrical 

bonding of a support bracket for a diffuser 

assembly installed between Rib 1 and Rib 2 

on the stringers of the Number 1 bottom skin 

panel, 


jlentini on PROD1PC65 with RULES
75308 Federal Register / Vol. 73, No. 239 / Thursday, December 11, 2008 / Rules and Regulations 

• Modification of bonding points, 

installation of additional bonding leads and 

other modifications of the Additional Center 

Tank (ACT), 

• Modification to increase the distance 

between metallic parts on the THS Trim 

Tank, 

• Installation of a bonding lead between 

the bonding tags on the Jettison valve 

actuator and drive assembly. 

This new AD supersedes EASA AD 2006– 

0322, taking over its requirements and: 

• Mandates SB [service bulletin] A330–28– 

3082 Revision 04 which introduces an 

additional work for some bonding points 

which were omitted from the center tank at 

original issue (action n°2 [paragraph (f)(2) of 

this AD]); 

• Mandates SB A340–28–4097 Revision 03 

which introduces an additional work by 

addition of electrical bondings omitted from 

previous revisions (action n°2); 

• Introduces an extension of the required 

compliance time to perform action n°4 for 

those aircraft already compliant with 

AIRBUS AOT 55–03 dated 22 August 1996 

(‘‘solution A’’), mandated by DGAC 

[Direction Ge ́ne ́rale de l’Aviation Civile] AD 

F–1996–178–049(B) R1 and DGAC AD F– 

1996–177–038(B) with a compliance time of 

November 15th, 1996; 

• Refers to the latest revision of certain 

AIRBUS SBs. 

The unsafe condition is the potential of 

ignition sources inside fuel tanks, 

which, in combination with flammable 

fuel vapors, could result in fuel tank 

explosions and consequent loss of the 

airplane. You may obtain further 

information by examining the MCAI in 

the AD docket. 

Explanation of New Service 

Information 

Airbus has issued Mandatory Service 

Bulletin A330–28–3082, Revision 05, 

including Appendix 1, dated May 27, 

2008. We referred to Revision 04 of that 

service bulletin, dated August 3, 2007, 

as the appropriate source of service 

information for accomplishing certain 

actions specified in the supplemental 

NPRM. Revision 05 of the service 

bulletin was issued to delete 

information relating to the bonding of a 

bracket at Stringer 14 between Rib 1 and 

Rib 2, which is not applicable to the 

Model A330 airplanes affected by that 

service bulletin. Revision 05 also 

includes additional kits and other minor 

editorial changes. No additional work is 

required for airplanes modified in 

accordance with Revision 04. 

We have changed Table 1 of this AD 

to include a reference to Revision 05, in 

addition to Revision 04, of Airbus 

Mandatory Service Bulletin A330–28– 

3082 for defining the applicability of 

certain paragraphs. We have also 

changed paragraphs (f)(2)(i) and 

(f)(2)(iii) of this AD to specify Revision 

05 of the service bulletin as the 

appropriate source of service 

information for doing the actions in 

those paragraphs, and we have changed 

Table 2 of this AD to list Revision 04 of 

the service bulletin as acceptable for 

accomplishment of the actions before 

the effective date of this AD. Finally, we 

have changed Table 3 of this AD to 

include Revision 05 of the service 

bulletin in the list of related service 

information. 

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 

with the changes described previously. 

We determined that these changes will 

not increase the economic burden on 

any operator or increase the scope of the 

AD. 

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. 

Costs of Compliance 

We estimate that this AD will affect 

28 products of U.S. registry. We also 

estimate that it will take about 670 

work-hours per product to comply with 

the basic requirements of this AD. The 

average labor rate is $80 per work-hour. 

Required parts will cost about $2,718 

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 parts. 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 the U.S. operators to be 

$1,576,904, or $56,318 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. 


jlentini on PROD1PC65 with RULES
Federal Register / Vol. 73, No. 239 / Thursday, December 11, 2008 / Rules and Regulations 75309 

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: 

2008–25–02 Airbus: Amendment 39–15760. 

Docket No. FAA–2007–27739; 

Directorate Identifier 2006–NM–250–AD. 

Effective Date 

(a) This airworthiness directive (AD) 

becomes effective January 15, 2009. 

Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to all Airbus Model 

A330, A340–200, and A340–300 airplanes, 

all certified models, all serial numbers, 

certificated in any category. 

Subject 

(d) Air Transport Association (ATA) of 

America Codes 28: Fuel, and 55: Stabilizers. 

Reason 

(e) The mandatory continuing 

airworthiness information (MCAI) states: 

[T]he FAA published SFAR 88 (Special 

Federal Aviation Regulation 88). 

By mail referenced 04/00/02/07/01–L296 

of March 4th, 2002 and 04/00/02/07/03–L024 

of February 3rd, 2003, the JAA (Joint 

Aviation Authorities) recommended to the 

National Aviation Authorities (NAA) the 

application of a similar regulation. 

The aim of this regulation is to require all 

holders of type certificates for passenger 

transport aircraft certified after January 1st, 

1958 with a capacity of 30 passengers or 

more, or a payload of 3,402 kg or more, to 

carry out a definition review against 

explosion hazards. 

Consequently, the following measures [are] 

rendered mandatory * * *: 

• [inspection and] replacement [if 

necessary] of the white P-clips by blue Pclips which are more fuel resistant remove 

the risks of fuel quantity indicator (FQI) and 

fuel level sensor system (FLSS) harnesses 

chafing against the metallic part of the P-clip, 

• Modification of electrical bonding of 

equipment installed in fuel tanks in order to 

re-establish the conformity with the design 

definition by introducing additional bonding 

leads, electrical bonding points and electrical 

bonding of a support bracket for a diffuser 

assembly installed between Rib 1 and Rib 2 

on the stringers of the Number 1 bottom skin 

panel, 

• Modification of bonding points, 

installation of additional bonding leads and 

other modifications of the Additional Center 

Tank (ACT), 

• Modification to increase the distance 

between metallic parts on the THS 

(trimmable horizontal stabilizer) Trim Tank, 

• Installation of a bonding lead between 

the bonding tags on the Jettison valve 

actuator and drive assembly. 

This new AD supersedes EASA AD 2006– 

0322, taking over its requirements and: 

• Mandates SB [service bulletin] A330–28– 

3082 Revision 04 which introduces an 

additional work for some bonding points 

which were omitted from the center tank at 

original issue (action n°2 [paragraph (f)(2) of 

this AD]); 

• Mandates SB A340–28–4097 Revision 03 

which introduces an additional work by 

addition of electrical bondings omitted from 

previous revisions (action n°2); 

• Introduces an extension of the required 

compliance time to perform action n°4 for 

those aircraft already compliant with 

AIRBUS AOT 55–03 dated 22 August 1996 

(‘‘solution A’’), mandated by DGAC 

[Direction Ge ́ne ́rale de l’Aviation Civile] AD 

F–1996–178–049(B) R1 and DGAC AD F– 

1996–177–038(B) with a compliance time of 

November 15th, 1996; 

• Refers to the latest revision of certain 

AIRBUS SBs. 

The unsafe condition is the potential of 

ignition sources inside fuel tanks, which, in 

combination with flammable fuel vapors, 

could result in fuel tank explosions and 

consequent loss of the airplane. 

Actions and Compliance 

(f) Unless already done, do the actions in 

paragraphs (f)(1), (f)(2), (f)(3), (f)(4), and (f)(5) 

of this AD for the applicable airplanes 

identified in Table 1 of this AD. 

TABLE 1—APPLICABLE PARAGRAPHS BY MODEL

These airplane models— Except airplanes— Are affected by these paragraphs of this AD— 

Model A330, A340–200, and A340–330 airplanes.On which Airbus Modification 47634 has been 

embodied in production.

(f)(1). 

• On which both Airbus Modifications 49135 

and 49630 have been embodied in production.

(f)(2)(i), except as provided by paragraphs 

(f)(2)(ii) and (f)(2)(iii) of this AD. 

• Both Airbus Modifications 51825 and 55118 

have been embodied in production.

• That have been modified in-service in accordance with both Airbus Mandatory Service Bulletin A330–28–3082, Revision 04, including Appendix 01, dated August 3, 2007, 

or Revision 05, including Appendix 1, dated 

May 27, 2008; and Airbus Mandatory Service Bulletin A330–28–3101, Revision 01, 

dated October 11, 2006.

• That have been modified in-service in accordance with both Airbus Mandatory Service Bulletin A340–28–4097, Revision 03, including Appendix 01, dated July 3, 2007; 

and Airbus Mandatory Service Bulletin 

A340–28–4118, Revision 02, dated July 10, 

2007.


jlentini on PROD1PC65 with RULES
75310 Federal Register / Vol. 73, No. 239 / Thursday, December 11, 2008 / Rules and Regulations 

TABLE 1—APPLICABLE PARAGRAPHS BY MODEL—Continued 

These airplane models— Except airplanes— Are affected by these paragraphs of this AD— 

Model A330 airplanes on which the actions 

specified in Airbus Service Bulletin A330– 

28–3082, dated June 14, 2004, have been 

accomplished before the effective date of 

this AD; and Model A340–200 and A340– 

300 airplanes on which the actions specified 

in Airbus Service Bulletin A340–28–4097, 

dated June 14, 2004, Revision 01, dated 

March 3, 2005, or Airbus Mandatory Service 

Bulletin A340–28–4097, Revision 02, dated 

August 16, 2006, have been accomplished 

before the effective date of this AD.

• On which both Airbus Modifications 49135 

and 49630 have been embodied in production.

• Both Airbus Modifications 51825 and 55118 

have been embodied in production.

• That have been modified in-service in accordance with both Airbus Mandatory Service Bulletin A330–28–3082, Revision 04, including Appendix 01, dated August 3, 2007, 

or Revision 05, including Appendix 1, dated 

May 27, 2008; and Airbus Mandatory Service Bulletin A330–28–3101, Revision 01, 

dated October 11, 2006.

(f)(2)(ii) and (f)(2)(iii). 

• That have been modified in-service in accordance with both Airbus Mandatory Service Bulletin A340–28–4097, Revision 03, including Appendix 01, dated July 3, 2007, 

and Airbus Mandatory Service Bulletin 

A340–28–4118, Revision 02, dated July 10, 

2007.

Model A340–200 and A340–300 airplanes that 

have the ACT embodied in production or in 

service (Airbus Modification 42612, 44002, 

or 44005).

That have been modified in service by Airbus 

Mandatory Service Bulletin A340–28–4078, 

Revision 01, dated January 25, 2007.

(f)(3). 

Model A340–200 and A340–300 airplanes ....... • On which Airbus Modification 44252 has 

been embodied in production.

(f)(4)(i), except as provided by paragraph 

(f)(4)(ii) of this AD. 

• That have been modified in-service in accordance with Airbus Service Bulletin A340– 

55–4017, dated August 20, 1996; Revision 

1, dated February 12, 2007; or Revision 02, 

dated March 16, 2007.

Model A330–301, –321, –322, –341, –342 airplanes.• On which Airbus Modification 44252 has 

been embodied in production.

(f)(4)(i), except as provided by paragraph 

(f)(4)(ii) of this AD. 

• That have been modified in-service in accordance with Airbus Service Bulletin A330– 

55–3016, dated August 20, 1996; Revision 

1 dated February 12, 1997; or Revision 02, 

dated March 16, 2007.

Model A330–301, –321, –322, –341, –342 airplanes; and Model A340–200 and A340–300 

airplanes.

On which the improvement of the THS lightning strike protection has already been performed before the effective date of this AD 

in accordance with Airbus A330/A340 All 

Operators Telex 55–03, dated August 22, 

1996 (‘‘solution A’’), mandated by Direction 

Ge ́ne ́rale de l’Aviation Civile (DGAC) Airworthiness Directive F–1996–178–049(B) 

R1, and DGAC Airworthiness Directive F– 

1996–177–038(B), with a compliance time 

of November 15, 1996.

(f)(4)(ii). 

Model A340–200 and A340–300 airplanes ....... • On which Airbus Modification 46142 has 

been embodied in production.

(f)(5). 

• That have been modified in-service in accordance with Airbus Mandatory Service 

Bulletin A340–28–4073, Revision 02, dated 

March 8, 2007.

(1) Within 24 months after the effective 

date of this AD, do a detailed visual 

inspection of the P-clips in the wings and 

center fuel tanks, and apply the applicable 

corrective actions, in accordance with the 

applicable instructions of Airbus Mandatory 

Service Bulletin A330–28–3092, Revision 01, 

dated December 14, 2005; or Airbus 

Mandatory Service Bulletin A340–28–4107, 

Revision 01, dated December 14, 2005. 

(2) Do the requirements of paragraphs 

(f)(2)(i), (f)(2)(ii), and (f)(2)(iii) of this AD, as 

applicable, at the times specified in those 

paragraphs. 

(i) For airplanes affected by this paragraph, 

as specified in Table 1 of this AD: Within 24 

months after the effective date of this AD, 

modify the electrical bonding of the 

equipment installed in fuel tanks, in 

accordance with both Airbus Mandatory 

Service Bulletin A330–28–3082, Revision 05, 

including Appendix 1, dated May 27, 2008, 

and Airbus Mandatory Service Bulletin 

A330–28–3101, Revision 01, dated October 

11, 2006; or both Airbus Mandatory Service 

Bulletin A340–28–4097, Revision 03, 

including Appendix 01, dated July 3, 2007, 

and Airbus Mandatory Service Bulletin 

A340–28–4118, Revision 02, dated July 10, 

2007; as applicable. 

(ii) For airplanes affected by this 

paragraph, as specified in Table 1 of this AD: 

Within 24 months after the effective date of 

this AD, modify the electrical bonding of the 

equipment installed in fuel tanks, in 

accordance with Airbus Mandatory Service 

Bulletin A330–28–3101, Revision 01, dated 

October 11, 2006; or Airbus Mandatory 

Service Bulletin A340–28–4118, Revision 02, 

dated July 10, 2007; as applicable. 

(iii) For airplanes affected by this 

paragraph, as specified in Table 1 of this AD: 


jlentini on PROD1PC65 with RULES
Federal Register / Vol. 73, No. 239 / Thursday, December 11, 2008 / Rules and Regulations 75311 

Within 48 months after the effective date of 

this AD, do the additional work specified in 

Airbus Mandatory Service Bulletin A330–28– 

3082, Revision 05, including Appendix 1, 

dated May 27, 2008; or Airbus Mandatory 

Service Bulletin A340–28–4097, Revision 03, 

including Appendix 01, dated July 3, 2007; 

in accordance with the accomplishment 

instructions of those service bulletins, as 

applicable. 

(3) Within 24 months after the effective 

date of this AD, modify the electrical bonding 

in the ACT in accordance with the 

Accomplishment Instructions of Airbus 

Mandatory Service Bulletin A340–28–4078, 

Revision 01, dated January 25, 2007. 

(4) Within 24 months after the effective 

date of this AD, do the requirements of 

paragraphs (f)(4)(i) and (f)(4)(ii), as 

applicable. 

(i) For airplanes affected by this paragraph, 

as specified in Table 1 of this AD: Within 24 

months after the effective date of this AD, 

increase the distance between metallic parts 

on the THS trim tank in accordance with the 

Accomplishment Instructions of Airbus 

Mandatory Service Bulletin A330–55–3016, 

Revision 02, March 16, 2007; or Airbus 

Mandatory Service Bulletin A340–55–4017, 

Revision 02, dated March 16, 2007; as 

applicable. 

(ii) For airplanes affected by this 

paragraph, as specified in Table 1 of this AD: 

At the first THS removal from the aircraft 

done for any reason after the effective date 

of this AD (e.g., fuselage stress jacking, and 

repair) when the airplane is on a support tool 

(lifting and resting point fittings must be 

installed), or at the time of the first 

maintenance task that requires the use of 

THS lifting and resting point fittings, 

whichever occurs earlier, increase the 

distance between metallic parts on the THS 

trim tank in accordance with the 

Accomplishment Instructions of Airbus 

Mandatory Service Bulletin A330–55–3016, 

Revision 02, March 16, 2007; or Airbus 

Mandatory Service Bulletin A340–55–4017, 

Revision 02, dated March 16, 2007; as 

applicable. 

(5) Within 24 months after the effective 

date of this AD, install a bonding lead 

between the bonding tags on the jettison 

valve actuator and drive assembly in 

accordance with the instructions of Airbus 

Mandatory Service Bulletin A340–28–4073, 

Revision 02, dated March 8, 2007. 

(6) Actions done before the effective date 

of this AD in accordance with the service 

bulletins listed in Table 2 of this AD are 

acceptable for compliance with the 

corresponding requirements of this AD. 

TABLE 2—CREDIT SERVICE BULLETINS

Airbus Service information Revision level Date Corresponding paragraphs 

Mandatory Service Bulletin A330–28–3082 ......... 02 ..................... August 11, 2006 ........... (f)(2)(i) of this AD. 

Mandatory Service Bulletin A330–28–3082 ......... 03 ..................... November 15, 2006 ..... (f)(2)(i) and (f)(2)(iii) of this AD. 

Mandatory Service Bulletin A330–28–3082 ......... 04 ..................... August 3, 2007 ............. (f)(2)(i) and (f)(2)(iii) of this AD. 

Mandatory Service Bulletin A330–28–3101 ......... Original ............. June 5, 2006 ................ (f)(2)(i) and (f)(2)(ii) of this AD. 

Mandatory Service Bulletin A340–28–4118 ......... Original ............. June 5, 2006 ................ (f)(2)(i) and (f)(2)(ii) of this AD. 

Mandatory Service Bulletin A340–28–4118 ......... 01 ..................... October 11, 2006 ......... (f)(2)(i) and (f)(2)(ii) of this AD. 

Service Bulletin A330–28–3082 ........................... 01 ..................... March 2, 2005 .............. (f)(2)(i) of this AD.

Service Bulletin A330–55–3016 ........................... Original ............. August 20, 1996 ........... (f)(4)(i) and (f)(4)(ii) of this AD. 

Service Bulletin A330–55–3016 ........................... 1 ....................... February 12, 1997 ....... (f)(4)(i) and (f)(4)(ii) of this AD. 

Service Bulletin A340–28–4073 ........................... Original ............. May 14, 1998 ............... (f)(5) of this AD. 

Service Bulletin A340–28–4073 ........................... 01 ..................... October 9, 1998 ........... (f)(5) of this AD. 

Service Bulletin A340–28–4078 ........................... Original ............. March 17, 2000 ............ (f)(3) of this AD. 

Service Bulletin A340–55–4017 ........................... Original ............. August 20, 1996 ........... (f)(4)(i) and (f)(4)(ii) of this AD. 

Service Bulletin A340–55–4017 ........................... 1 ....................... February 12, 1997 ....... (f)(4)(i) and (f)(4)(ii) of this AD. 

FAA AD Differences 

Note 1: This AD differs from the MCAI 

and/or service information as follows: No 

differences. 

Other FAA AD Provisions 

(g) The following provisions also apply to 

this AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, ANM–116, 

International Branch, 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: Tim Backman, 

Aerospace Engineer, ANM–116, International 

Branch, Transport Airplane Directorate, FAA, 

1601 Lind Ave. SW., Renton, Washington, 

98057–3356, telephone (425) 227–2797; 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 FAAapproved 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 

(h) Refer to MCAI European Aviation 

Safety Agency (EASA) Airworthiness 

Directive 2007–0278, dated November 5, 

2007 [Corrected: November 8, 2007], and the 

service bulletins in Table 3 of this AD, for 

related information. 

TABLE 3—RELATED SERVICE BULLETINS

Airbus Mandatory Service Bulletin Revision level Date 

A330–28–3082, including Appendix 1 ................................................................................................ 05 May 27, 2008. 

A330–28–3092, excluding Appendix 01 ............................................................................................. 01 December 14, 2005. 

A330–28–3101 .................................................................................................................................... 01 October 11, 2006. 

A330–55–3016 .................................................................................................................................... 02 March 16, 2007. 

A340–28–4073 .................................................................................................................................... 02 March 8, 2007. 

A340–28–4078 .................................................................................................................................... 01 January 25, 2007. 

A340–28–4097, including Appendix 01 .............................................................................................. 03 July 3, 2007. 

A340–28–4107, excluding Appendix 01 ............................................................................................. 01 December 14, 2005. 

A340–28–4118 .................................................................................................................................... 02 July 10, 2007. 

A340–55–4017 .................................................................................................................................... 02 March 16, 2007. 


jlentini on PROD1PC65 with RULES
75312 Federal Register / Vol. 73, No. 239 / Thursday, December 11, 2008 / Rules and Regulations 

Material Incorporated by Reference 

(i) You must use the service information 

specified in Table 4 of this AD 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—Airworthiness 

Office—EAL, 1 Rond Point Maurice Bellonte, 

31707 Blagnac Cedex, France; fax +33 5 61 

93 45 80, e-mail airworthiness.A330- 

A340@airbus.com; Internet http:// 

www.airbus.com. 

(3) You may review copies of the service 

information that is incorporated by reference 

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 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/ 

cfr/ibr-locations.html. 

TABLE 4—MATERIAL INCORPORATED BY REFERENCE

Airbus Mandatory Service Bulletin Revision level Date 

A330–28–3082, including Appendix 1 ................................................................................................ 05 May 27, 2008. 

A330–28–3092, excluding Appendix 01 ............................................................................................. 01 December 14, 2005. 

A330–28–3101 .................................................................................................................................... 01 October 11, 2006. 

A330–55–3016 .................................................................................................................................... 02 March 16, 2007. 

A340–28–4073 .................................................................................................................................... 02 March 8, 2007. 

A340–28–4078 .................................................................................................................................... 01 January 25, 2007. 

A340–28–4097, including Appendix 01 .............................................................................................. 03 July 3, 2007. 

A340–28–4107, excluding Appendix 01 ............................................................................................. 01 December 14, 2005. 

A340–28–4118 .................................................................................................................................... 02 July 10, 2007. 

A340–55–4017 .................................................................................................................................... 02 March 16, 2007. 

Issued in Renton, Washington, on 

November 26, 2008. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. E8–29076 Filed 12–10–08; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2008–1007; Directorate 

Identifier 2008–NM–135–AD; Amendment 

39–15761; AD 2008–25–03] 

RIN 2120–AA64 

Airworthiness Directives; Bombardier 

Model CL–600–2C10 (Regional Jet 

Series 700, 701 & 702) Airplanes and 

Model CL–600–2D24 (Regional Jet 

Series 900) 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: 

Bombardier Aerospace has completed a 

system safety review of the CL–600–2C10/ 

CL–600–2D24 aircraft fuel system against 

new fuel tank safety standards. * * * 

The assessment showed that due to the 

close proximity of intrinsically safe fuel 

system wiring with other wiring, a single 

failure from wire chafing at various locations 

of the fuselage could result in an ignition 

source inside the fuel tank. In addition, 

chafing of the temperature sensor wiring 

against the high power wiring in the avionics 

compartment could lead to overheating of the 

temperature sensor and hot surface ignition. 

The presence of an ignition source inside the 

fuel tank could result in a fuel tank 

explosion. 

We are issuing this AD to require 

actions to correct the unsafe condition 

on these products. 

DATES: This AD becomes effective 

January 15, 2009. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of January 15, 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: 

Rocco Viselli, Aerospace Engineer, 

Airframe and Propulsion Branch, ANE– 

171, FAA, New York Aircraft 

Certification Office, 1600 Stewart 

Avenue, Suite 410, Westbury, New York 

11590; telephone (516) 228–7331; fax 

(516) 794–5531. 

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 September 23, 2008 (73 FR 

54749). That NPRM proposed to correct 

an unsafe condition for the specified 

products. The MCAI states: 

Bombardier Aerospace has completed a 

system safety review of the CL–600–2C10/ 

CL–600–2D24 aircraft fuel system against 

new fuel tank safety standards, introduced in 

Chapter 525 of the Airworthiness Manual 

through Notice of Proposed Amendment 

(NPA) 2002–043. The identified noncompliances were assessed using Transport 

Canada Policy Letter No. 525–001 to 

determine if mandatory corrective action was 

required. 

The assessment showed that due to the 

close proximity of intrinsically safe fuel 

system wiring with other wiring, a single 

failure from wire chafing at various locations 

of the fuselage could result in an ignition 

source inside the fuel tank. In addition, 

chafing of the temperature sensor wiring 

against the high power wiring in the avionics 

compartment could lead to overheating of the 

temperature sensor and hot surface ignition. 

The presence of an ignition source inside the 

fuel tank could result in a fuel tank 

explosion. 

To correct the unsafe condition, this 

directive mandates the installation of conduit 

and the addition of spacers to protect fuel 

tank wiring. 

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 


jlentini on PROD1PC65 with RULES