73486 Federal Register / Vol. 76, No. 229 / Tuesday, November 29, 2011 / Rules and Regulations 

applicable Gulfstream alert customer bulletin 

identified in table 1 of this AD: Do the 

actions required by paragraph (g)(3)(i) or 

(g)(3)(ii) of this AD. 

(i) Before further flight, remove the bottle, 

in accordance with the Accomplishment 

Instructions of the applicable Gulfstream 

alert customer bulletin identified in table 1 

of this AD. 

(ii) Before further flight, revise the 

limitations section of the applicable 

Gulfstream AFM specified in table 1 of this 

AD to include the information in Gulfstream 

GV/GV–SP AFM Supplement CE51 

628M001, Revision A, dated December 20, 

2010. This AFM supplement adds 

restrictions for APU usage. Operate the 

airplane thereafter according to the 

limitations in that AFM supplement. 

Note 2: This may be done by inserting a 

copy of Gulfstream GV/GV–SP AFM 

Supplement CE51 628M001, Revision A, 

dated December 20, 2010, in the applicable 

AFM. When information in this AFM 

supplement has been included in general 

revisions of the applicable AFM, the general 

revisions may be inserted in the applicable 

AFM, provided the relevant information in 

the general revision is identical to that in 

Gulfstream GV/GV–SP AFM Supplement 

CE51 628M001, Revision A, dated December 

20, 2010, and that AFM supplement may be 

removed. 

(h) Credit for Actions Accomplished in 

Accordance With Previous Service 

Information 

Actions accomplished before the effective 

date of this AD in accordance with 

Gulfstream V Alert Customer Bulletin 30, 

dated December 6, 2010, including 

Gulfstream GV/GV–SP AFM Supplement 

CE51 628M001, dated November 18, 2010 

(for Model GV airplanes); Gulfstream G550 

Alert Customer Bulletin 10, dated December 

6, 2010, including Gulfstream GV/GV–SP 

AFM Supplement CE51 628M001, dated 

November 18, 2010 (for Model GV airplanes); 

or G500 Alert Customer Bulletin 10, dated 

December 6, 2010, including Gulfstream GV/ 

GV–SP AFM Supplement CE51 628M001, 

dated November 18, 2010 (for Model GV 

airplanes), are acceptable for compliance 

with the corresponding actions required by 

paragraph (g) of this AD. 

(i) Parts Installation 

As of the effective date of this AD, no 

person may install a third fire extinguisher 

bottle in the APU fragment impact zone 

(rotor fragment impact zone) of any airplane. 

(j) No Reporting 

Although the service information specified 

in paragraphs (j)(1), (j)(2), and (j)(3) of this 

AD specify to submit certain information to 

the manufacturer, this AD does not include 

that requirement. 

(1) Gulfstream V Alert Customer Bulletin 

30A, dated December 20, 2010, including 

Gulfstream GV/GV–SP AFM Supplement 

CE51 628M001, Revision A, dated December 

20, 2010, (for Model GV airplanes). 

(2) Gulfstream G500 Alert Customer 

Bulletin 10A, dated December 20, 2010, 

including Gulfstream GV/GV–SP AFM 

Supplement CE51 628M001, Revision A, 

dated December 20, 2010, (for Model GV–SP 

(G500) airplanes). 

(3) Gulfstream G550 Alert Customer 

Bulletin 10A, dated December 20, 2010, 

including Gulfstream GV/GV–SP AFM 

Supplement CE51 628M001, Revision A, 

dated December 20, 2010, (for Model GV–SP 

(G550) airplanes). 

(k) Special Flight Permit 

Special flight permits, as described in 

Section 21.197 and Section 21.199 of the 

Federal Aviation Regulations (14 CFR 21.197 

and 21.199), may be issued to operate the 

airplane to a location where the requirements 

of this AD can be accomplished, provided the 

following conditions are met: 

(1) If an airplane is grounded due to a 

single generator failure, the APU may be 

operated during a ferry flight, provided no 

passengers are carried. 

(2) Only the minimum required flight-crew 

is allowed on any ferry flight. 

(l) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Atlanta 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. In accordance with 14 CFR 39.19, 

send your request to your principal inspector 

or local Flight Standards District Office, as 

appropriate. If sending information directly 

to the manager of the ACO, send it to the 

attention of the person identified in the 

Related Information section of this AD. 

(2) Before using any approved AMOC, 

notify your appropriate principal inspector, 

or lacking a principal inspector, the manager 

of the local flight standards district office/ 

certificate holding district office. 

(m) Related Information 

For more information about this AD, 

contact Sanford Proveaux, Aerospace 

Engineer, Continued Operational Safety and 

Certificate Management Branch, ACE–102A, 

FAA, Atlanta Aircraft Certification Office 

(ACO), 1701 Columbia Avenue, College Park, 

Georgia 30337; telephone (404) 474–5566; fax 

(404) 474–5606; email: 

sanford.proveaux@faa.gov. 

(n) Material Incorporated by Reference 

(1) You must use the following service 

information to do the actions required by this 

AD, unless the AD specifies otherwise. The 

Director of the Federal Register approved the 

incorporation by reference (IBR) under 

5 U.S.C. 552(a) and 1 CFR part 51 of the 

following service information on the date 

specified: 

(2) Gulfstream G500 Alert Customer 

Bulletin 10A, dated December 20, 2010, 

including Gulfstream GV/GV–SP airplane 

flight manual (AFM) Supplement CE51 

628M001, Revision A, dated December 20, 

2010, approved for IBR January 3, 2012. 

(3) Gulfstream G550 Alert Customer 

Bulletin 10A, dated December 20, 2010, 

including Gulfstream GV/GV–SP AFM 

Supplement CE51 628M001, Revision A, 

dated December 20, 2010, approved for IBR 

January 3, 2012. 

(4) Gulfstream V Alert Customer Bulletin 

30A, dated December 20, 2010, including 

Gulfstream GV/GV–SP AFM Supplement 

CE51 628M001, Revision A, dated December 

20, 2010, approved for IBR January 3, 2012. 

(5) For service information identified in 

this AD, contact Gulfstream Aerospace 

Corporation, Technical Publications Dept., 

P.O. Box 2206, Savannah, Georgia 31402– 

2206; telephone (800) 810–4853; fax (912) 

965–3520; e-mail pubs@gulfstream.com; 

Internet http://www.gulfstream.com/ 

product_support/technical_pubs/pubs/ 

index.htm. You may review copies of the 

referenced service information at the FAA. 

(6) 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. 

(7) 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 an NARA facility, 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 8, 2011. 

Kalene C. Yanamura, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2011–29806 Filed 11–28–11; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2011–1232; Directorate 

Identifier 2011–NM–039–AD; Amendment 

39–16873; AD 2011–24–09] 

RIN 2120–AA64 

Airworthiness Directives; Airbus 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule; request for 

comments. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for certain 

Airbus Model A340–200 and -300 series 

airplanes. 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: 

[T]he FAA published SFAR 88 (Special 

Federal Aviation Regulation 88) [(66 FR 

23086, May 7, 2001)]. 


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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 [EASA] regulation is to 

require * * * a definition review against 

explosion hazards. 

* * * * * 

This AD requires inspections to verify 

electrical bonding to prevent 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. This AD requires 

actions that are intended to address the 

unsafe condition described in the MCAI. 

DATES: This AD becomes effective 

December 14, 2011. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in the AD 

as of December 14, 2011. 

We must receive comments on this 

AD by January 13, 2012. 

ADDRESSES: You may send comments by 

any of the following methods: 

• Federal eRulemaking Portal: Go to 

http://www.regulations.gov. Follow the 

instructions for submitting comments. 

• Fax: (202) 493–2251. 

• Mail: U.S. Department of 

Transportation, Docket Operations, 

M–30, West Building Ground Floor, 

Room W12–140, 1200 New Jersey 

Avenue SE., Washington, DC 20590. 

• Hand Delivery: U.S. Department of 

Transportation, Docket Operations, 

M–30, West Building Ground Floor, 

Room W12–140, 1200 New Jersey 

Avenue SE., Washington, DC, between 9 

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

Friday, except Federal holidays. 

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 this AD, 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. 

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 

The European Aviation Safety Agency 

(EASA), which is the Technical Agent 

for the Member States of the European 

Community, has issued EASA 

Airworthiness Directive 2010–0232, 

dated November 12, 2010 (referred to 

after this as ‘‘the MCAI’’), to correct an 

unsafe condition for the specified 

products. The MCAI states: 

[T]he FAA published SFAR 88 (Special 

Federal Aviation Regulation 88) [(66 FR 

23086, May 7, 2001)]. 

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 transport 

aircraft certified after 01 January 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. 

To be compliant with SFAR88/JAA INT/ 

POL 25/12 requirements, this [EASA] AD 

requires, for operators who have already 

embodied the Revision 03 or any previous 

revision of Airbus SB A340–28–4097 on 

aeroplanes which were previously in SB 

Configurations 02 or 03 [required by FAA AD 

2008–25–02, Amendment 39–15760 (73 FR 

75307, December 11, 2008)], an inspection to 

verify if the electrical bonding of the water 

drain system (Trim Tank) and the electrical 

bonding of the ventilation intake system were 

correctly accomplished or need additional 

work associated to the aeroplane 

configuration. 

* * * * * 

Additional work could involve 

modifying or installing certain bonding 

points (such as pipe clamps, screws, 

attachment fittings, restrictor valves, 

flame arrestors, and pipes); doing 

electrical bonding of the wing fuel 

pumps, the water drain system between 

certain ribs, a water drain system and 

the ventilation intake system; 

depending on configuration. The 

additional work required by this AD is 

in addition to the requirements of AD 

2008–25–02, Amendment 39–15760 (73 

FR 75307, December 11, 2008). 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. 

The FAA has examined the 

underlying safety issues involved in fuel 

tank explosions on several large 

transport airplanes, including the 

adequacy of existing regulations, the 

service history of airplanes subject to 

those regulations, and existing 

maintenance practices for fuel tank 

systems. As a result of those findings, 

we issued a regulation titled ‘‘Transport 

Airplane Fuel Tank System Design 

Review, Flammability Reduction and 

Maintenance and Inspection 

Requirements’’ (66 FR 23086, May 7, 

2001). In addition to new airworthiness 

standards for transport airplanes and 

new maintenance requirements, this 

rule included Special Federal Aviation 

Regulation No. 88 (‘‘SFAR 88,’’ 

Amendment 21–78, and subsequent 

Amendments 21–82 and 21–83). 

Among other actions, SFAR 88 (66 FR 

23086, May 7, 2001) requires certain 

type design (i.e., type certificate (TC) 

and supplemental type certificate (STC)) 

holders to substantiate that their fuel 

tank systems can prevent ignition 

sources in the fuel tanks. This 

requirement applies to type design 

holders for large turbine-powered 

transport airplanes and for subsequent 

modifications to those airplanes. It 

requires them to perform design reviews 

and to develop design changes and 

maintenance procedures if their designs 

do not meet the new fuel tank safety 

standards. As explained in the preamble 

to the rule, we intended to adopt 

airworthiness directives to mandate any 

changes found necessary to address 

unsafe conditions identified as a result 

of these reviews. 

In evaluating these design reviews, we 

have established four criteria intended 

to define the unsafe conditions 

associated with fuel tank systems that 

require corrective actions. The 

percentage of operating time during 

which fuel tanks are exposed to 

flammable conditions is one of these 

criteria. The other three criteria address 

the failure types under evaluation: 

Single failures, single failures in 

combination with a latent condition(s), 

and in-service failure experience. For all 

four criteria, the evaluations included 

consideration of previous actions taken 

that may mitigate the need for further 

action. 

The Joint Aviation Authorities (JAA) 

has issued a regulation that is similar to 

SFAR 88 (66 FR 23086, May 7, 2001). 

(The JAA is an associated body of the 

European Civil Aviation Conference 

(ECAC) representing the civil aviation 

regulatory authorities of a number of 

European States who have agreed to cooperate in developing and 

implementing common safety regulatory 

standards and procedures.) Under this 

regulation, the JAA stated that all 

members of the ECAC that hold type 

certificates for transport category 

airplanes are required to conduct a 

design review against explosion risks. 

We have determined that the actions 

identified in this AD are necessary to 


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reduce 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. 

Relevant Service Information 

Airbus has issued Mandatory Service 

Bulletin A340–28–4097, Revision 05, 

including Appendix 1, dated June 3, 

2010. The actions described in this 

service information are intended to 

correct the unsafe condition identified 

in the MCAI. 

FAA’s Determination and Requirements 

of This AD 

This product has been approved by 

the aviation authority of another 

country, and is approved for operation 

in the United States. Pursuant to our 

bilateral agreement with the State of 

Design Authority, we have been notified 

of the unsafe condition described in the 

MCAI and service information 

referenced above. We are issuing this 

AD because we evaluated all pertinent 

information and determined the unsafe 

condition exists and is likely to exist or 

develop on other products of the same 

type design. 

There are no products of this type 

currently registered in the United States. 

However, this rule is necessary to 

ensure that the described unsafe 

condition is addressed if any of these 

products are placed on the U.S. Register 

in the future. 

Differences Between the 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 FAA policies. 

Any such differences are highlighted in 

a NOTE within the AD. 

FAA’s Determination of the Effective 

Date 

Since there are currently no domestic 

operators of this product, notice and 

opportunity for public comment before 

issuing this AD are unnecessary. 

Comments Invited 

This AD is a final rule that involves 

requirements affecting flight safety, and 

we did not precede it by notice and 

opportunity for public comment. We 

invite you to send any written relevant 

data, views, or arguments about this AD. 

Send your comments to an address 

listed under the ADDRESSES section. 

Include ‘‘Docket No. FAA–2011–1232; 

Directorate Identifier 2011–NM–039– 

AD’’ at the beginning of your comments. 

We specifically invite comments on the 

overall regulatory, economic, 

environmental, and energy aspects of 

this AD. We will consider all comments 

received by the closing date and may 

amend this AD because of those 

comments. 

We will post all comments we 

receive, without change, to http:// 

www.regulations.gov, including any 

personal information you provide. We 

will also post a report summarizing each 

substantive verbal contact we receive 

about this AD. 

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), 

(3) Will not affect intrastate aviation 

in Alaska, and 

(4) 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. 

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: 

2011–24–09 Airbus: Amendment 39–16873. 

Docket No. FAA–2011–1232; Directorate 

Identifier 2011–NM–039–AD. 

Effective Date 

(a) This airworthiness directive (AD) 

becomes effective December 14, 2011. 

Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to Airbus Model A340– 

211, –212, –213, –311, –312 and –313 

airplanes, certificated in any category, all 

manufacturer serial numbers, on which 

Airbus modification 41600 has been 

embodied in production and Airbus Service 

Bulletin A340–28–4097, dated June 14, 2004; 

Revision 01, dated March 3, 2005; Revision 

02, dated August 16, 2006; or Revision 03, 

dated July 3, 2007; has been embodied in 

service, except airplanes on which Airbus 

modification 49135 has been embodied in 

production. 

Subject 

(d) Air Transport Association (ATA) of 

America Code 28: Fuel. 

Reason 

(e) The mandatory continued airworthiness 

information (MCAI) states: 

[T]he FAA published SFAR 88 (Special 

Federal Aviation Regulation 88) [(66 FR 

23086, May 7, 2001)]. 

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 [EASA] regulation is to 

require * * * a definition review against 

explosion hazards. 

* * * * * 

This AD requires inspections to verify 

electrical bonding to prevent the potential of 

ignition sources inside fuel tanks, which, in 


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Federal Register / Vol. 76, No. 229 / Tuesday, November 29, 2011 / Rules and Regulations 73489 

combination with flammable fuel vapors, 

could result in fuel tank 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 the 

actions have already been done. 

Actions 

(g) Within 24 months after the effective 

date of this AD, do a detailed inspection of 

the electrical bonding for the water drain 

system (trim tank) and the ventilation intake 

system to verify whether it is equivalent to 

the electrical bonding done in accordance 

with the Accomplishment Instructions of 

Airbus Mandatory Service Bulletin A340–28– 

4097, Revision 05, including Appendix 1, 

dated June 3, 2010. 

(h) If, during the inspection required by 

paragraph (g) of this AD, the electrical 

bonding of the water drain system and the 

ventilation intake system is found to be not 

equivalent to the electrical bonding done in 

accordance with the Accomplishment 

Instructions of Airbus Mandatory Service 

Bulletin A340–28–4097, Revision 05, 

including Appendix 1, dated June 3, 2010: 

Within 24 months after the effective date of 

this AD, modify the electrical bonding 

associated with the airplane configuration in 

accordance with paragraph 3.B.(11) or 

3.B.(12), as applicable, of the 

Accomplishment Instructions of Airbus 

Mandatory Service Bulletin A340–28–4097, 

Revision 05, including Appendix 1, dated 

June 3, 2010. 

(i) A review of the airplane maintenance 

records is acceptable in lieu of the inspection 

required by paragraph (g) of this AD provided 

that the accomplishment of the electrical 

bonding for the water drain system (trim 

tank) and the ventilation intake system can 

be conclusively identified as performed in 

accordance with Airbus Mandatory Service 

Bulletin A340–28–4097, Revision 05, 

including Appendix 1, dated June 3, 2010. 

FAA AD Differences 

Note 1: This AD differs from the MCAI 

and/or service information as follows: No 

differences. 

Other FAA AD Provisions 

(j) 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. 

In accordance with 14 CFR 39.19, send your 

request to your principal inspector or local 

Flight Standards District Office, as 

appropriate. If sending information directly 

to the International Branch, send it to ATTN: 

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. Information may be emailed to: 9- 

ANM-116-AMOC-REQUESTS@faa.gov. 

Before using any approved AMOC, notify 

your appropriate principal inspector, or 

lacking a principal inspector, the manager of 

the local flight standards district office/ 

certificate holding district office. The AMOC 

approval letter must specifically reference 

this AD. 

(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 

(k) Refer to Mandatory Continuing 

Airworthiness Information (MCAI) European 

Aviation Safety Agency (EASA) 

Airworthiness Directive 2010–0232, dated 

November 12, 2010; and Airbus Mandatory 

Service Bulletin A340–28–4097, Revision 05, 

including Appendix 1, dated June 3, 2010; 

for related information. 

Material Incorporated by Reference 

(l) You must use Airbus Mandatory Service 

Bulletin A340–28–4097, Revision 05, 

including Appendix 1, dated June 3, 2010, 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; telephone +33 

5 61 93 36 96; fax +33 5 61 93 45 80; email 

airworthiness.A330-A340@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. 

(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 

November 14, 2011. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2011–30229 Filed 11–28–11; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2011–1261; Directorate 

Identifier 2011–NE–38–AD; Amendment 39– 

16875; AD 2011–24–11] 

RIN 2120–AA64 

Airworthiness Directives; Honeywell 

International Inc. Turbofan Engines 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule; request for 

comments. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for certain 

Honeywell International Inc. ALF502L– 

2C, ALF502R–3, ALF502R–3A, 

ALF502R–5, LF507–1F, and LF507–IH 

turbofan engines. This AD requires 

removing from service certain second 

stage high pressure compressor (HPC2) 

discs. This AD was prompted by a 

report of cracks found in an HPC2 disc 

during routine inspection. We are 

issuing this AD to prevent the affected 

discs from fracturing before reaching the 

currently published life limit. A disc 

fracture could result in an uncontained 

failure of the disc and damage to the 

airplane. 

DATES: This AD is effective December 

14, 2011. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in the AD 

as of December 14, 2011. 

We must receive comments on this 

AD by January 13, 2012. 

ADDRESSES: You may send comments, 

using the procedures found in 14 CFR 

11.43 and 11.45, by any of the following 

methods: 

• Federal eRulemaking Portal: Go to 

http://www.regulations.gov. Follow the 

instructions for submitting comments. 

• Fax: (202) 493–2251. 

• Mail: U.S. Department of 

Transportation, Docket Operations, 

M–30, West Building Ground Floor, 

Room W12–140, 1200 New Jersey 

Avenue SE., Washington, DC 20590. 

• Hand Delivery: U.S. Department of 

Transportation, Docket Operations, 

M–30, West Building Ground Floor, 

Room W12–140, 1200 New Jersey 

Avenue SE., Washington, DC 20590, 

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

through Friday, except Federal holidays. 

For service information identified in 

this AD, contact Honeywell 

International Inc., P.O. Box 52181, 

Phoenix, AZ 85072–2181, phone: (800) 

601–3099; Web site: http:// 


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