78524 Federal Register / Vol. 76, No. 243 / Monday, December 19, 2011 / Rules and Regulations 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2011–0918; Directorate 

Identifier 2011–NM–090–AD; Amendment 

39–16896; AD 2011–26–06] 

RIN 2120–AA64 

Airworthiness Directives; Airbus 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for Airbus 

Model A330–200 and –300 series 

airplanes, Model A340–200 and –300 

series airplanes, and Model A340–500 

and –600 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: 

During a pre-flight test before delivery of 

an aeroplane from the Airbus production 

line, a fault message was triggered on FDU1 

[fire detection unit]. 

Investigations by the supplier on the faulty 

FDU have identified a soldering quality issue 

on one of the internal cards. This quality 

issue resulted from a specific repair process 

that was applied to some FDU * * * during 

manufacturing. 

The FDU monitors the engine, Auxiliary 

Power Unit (APU) and Main Landing Gear 

(MLG) bay fire detection systems. 

This condition, if not corrected, may 

adversely affect the fire detection system 

performance in case of a fire in the area that 

is monitored by the faulty FDU, potentially 

resulting in an unsafe condition. 

* * * * * 

We are issuing this AD to require 

actions to correct the unsafe condition 

on these products. 

DATES: This AD becomes effective 

January 23, 2012. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in this AD 

as of January 23, 2012. 

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 September 14, 2011 (76 FR 

56680). That NPRM proposed to correct 

an unsafe condition for the specified 

products. The MCAI states: 

During a pre-flight test before delivery of 

an aeroplane from the Airbus production 

line, a fault message was triggered on FDU1. 

Investigations by the supplier on the faulty 

FDU have identified a soldering quality issue 

on one of the internal cards. This quality 

issue resulted from a specific repair process 

that was applied to some FDU Part Number 

(P/N) 3711–00 during manufacturing. 

The FDU monitors the engine, Auxiliary 

Power Unit (APU) and Main Landing Gear 

(MLG) bay fire detection systems. 

This condition, if not corrected, may 

adversely affect the fire detection system 

performance in case of a fire in the area that 

is monitored by the faulty FDU, potentially 

resulting in an unsafe condition. 

For the reasons described above, this 

[EASA] AD requires the identification and 

replacement of the affected FDU. 

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 (76 

FR 56680, September 14, 2011) or on the 

determination of the cost to the public. 

Conclusion 

We reviewed the relevant 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. 

Costs of Compliance 

We estimate that this AD will affect 

58 products of U.S. registry. We also 

estimate that it will take about 1 workhour per product to comply with the 

basic requirements of this AD. The 

average labor rate is $85 per work-hour. 

Required parts will cost about $0 per 

product. Replacement parts may be 

provided free of charge by the 

manufacturer. 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 

$4,930, or $85 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, 


srobinson on DSK4SPTVN1PROD with RULES
Federal Register / Vol. 76, No. 243 / Monday, December 19, 2011 / Rules and Regulations 78525 

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 (76 FR 56680, 

September 14, 2011), 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 adding 

the following new AD: 

2011–26–06 Airbus: Amendment 39–16896. 

Docket No. FAA–2011–0918; Directorate 

Identifier 2011–NM–090–AD. 

Effective Date 

(a) This airworthiness directive (AD) 

becomes effective January 23, 2012. 

Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to Airbus Model A330– 

201, –202, –203, –223, –223F, –243, and 

–243F airplanes; Model A330–301, –302, 

–303, –321, –322, –323, –341, –342, and –343 

airplanes; Model A340–211, –212, and –213 

airplanes; Model A340–311, –312, and –313 

airplanes; Model A340–541 airplanes; and 

Model A340–642 airplanes; certificated in 

any category; all serial numbers. 

Subject 

(d) Air Transport Association (ATA) of 

America Code 26: Fire Protection. 

Reason 

(e) The mandatory continuing 

airworthiness information (MCAI) states: 

During a pre-flight test before delivery of 

an aeroplane from the Airbus production 

line, a fault message was triggered on FDU1 

[fire detection unit]. 

Investigations by the supplier on the faulty 

FDU have identified a soldering quality issue 

on one of the internal cards. This quality 

issue resulted from a specific repair process 

that was applied to some FDU * * * during 

manufacturing. 

The FDU monitors the engine, Auxiliary 

Power Unit (APU) and Main Landing Gear 

(MLG) bay fire detection systems. 

This condition, if not corrected, may 

adversely affect the fire detection system 

performance in case of a fire in the area that 

is monitored by the faulty FDU, potentially 

resulting in an unsafe condition. 

* * * * * 

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 1,000 flight hours after the 

effective date of this AD: Do an inspection to 

identify the fire detection unit (FDU) part 

number (P/N) and serial number (S/N) of 

each engine, auxiliary power unit (APU), and 

MLG bay (for Model A340–500 and –600 

series airplanes only), as applicable, in 

accordance with the instructions of Airbus 

All Operators Telex (AOT) A330–26A3052, 

dated April 19, 2011 (for Model A330–200 

and –300 series airplanes); Airbus AOT 

A340–200/300–26A4044, dated April 19, 

2011 (for Model A340–200 and –300 series 

airplanes); or Airbus AOT A340–500/600– 

26A5024, dated April 19, 2011 (for Model 

A340–500 and –600 series airplanes). A 

review of maintenance records is acceptable 

in lieu of this inspection if the part number 

and serial number of the installed FDU can 

be conclusively determined from that review. 

(h) If during the inspection required by 

paragraph (g) of this AD, an FDU with P/N 

3711–00 is found installed and the serial 

number of the FDU is listed in table 1 of this 

AD: Before further flight, replace the FDU 

with a serviceable FDU, in accordance with 

the instructions of Airbus AOT A330– 

26A3052, dated April 19, 2011 (for Model 

A330–200 and –300 series airplanes); Airbus 

AOT A340–200/300–26A4044, dated April 

19, 2011 (for Model A340–200 and –300 

series airplanes); or Airbus AOT A340–500/ 

600–26A5024, dated April 19, 2011 (for 

Model A340–500 and –600 series airplanes). 

TABLE 1—AFFECTED P/N 3711–00 

FDUS

Serial numbers 

ZL0683 

ZL0718 

ZL0721 through ZL0725 inclusive 

ZL0727 

ZL0729 through ZL0731 inclusive 

ZL0736 

ZL0738 

ZL0740 

ZL0742 

ZL0743 

ZL0745 

ZL0747 

ZL0770 

ZL0772 

ZL0775 

ZL0788 

ZL0804 

Note 1: Some of the affected P/N 3711–00 

FDUs have been installed in production on 

certain airplanes, as indicated in table 2 of 

this AD. 

TABLE 2—FDUS INSTALLED IN PRODUCTION

Model A330–200 and –300 airplanes manufacturer 

serial numbers Position S/N 

1177 ................................................................................ ENG2 FDU (1WD2) ..................................................................................... ZL0683 

1191 ................................................................................ ENG2 FDU (1WD2) ..................................................................................... ZL0723 

1192 ................................................................................ ENG1 FDU (1WD1) .....................................................................................

ENG2 FDU (1WD2) .....................................................................................

ZL0721 

ZL0722 

1193 ................................................................................ APU FDU (13WG) ....................................................................................... ZL0718 

1195 ................................................................................ ENG1 FDU (1WD1) ..................................................................................... ZL0740 

1196 ................................................................................ ENG1 FDU (1WD1) .....................................................................................

ENG2 FDU (1WD2) .....................................................................................

APU FDU (13WG) .......................................................................................

ZL0742 

ZL0736 

ZL0743 

1198 ................................................................................ ENG2 FDU (1WD2) ..................................................................................... ZL0738 

1199 ................................................................................ APU FDU (13WG) ....................................................................................... ZL0731 

1200 ................................................................................ ENG1 FDU (1WD1) ..................................................................................... ZL0747 


srobinson on DSK4SPTVN1PROD with RULES
78526 Federal Register / Vol. 76, No. 243 / Monday, December 19, 2011 / Rules and Regulations 

TABLE 2—FDUS INSTALLED IN PRODUCTION—Continued 

Model A330–200 and –300 airplanes manufacturer 

serial numbers Position S/N 

1206 ................................................................................ ENG2 FDU (1WD2) ..................................................................................... ZL0770 

Parts Installation 

(i) As of the effective date of this AD, no 

person may install on any airplane, any P/N 

3711–00 FDU with a serial number listed in 

table 1 of this AD, unless the FDU has been 

reworked and re-identified by L’Hotellier as 

specified in the instructions in Airbus AOT 

A330–26A3052, dated April 19, 2011 (for 

Model A330–200 and –300 series airplanes); 

Airbus AOT A340–200/300–26A4044, dated 

April 19, 2011 (for Model A340–200 and 

–300 series airplanes); or Airbus AOT A340– 

500/600–26A5024, dated April 19, 2011 (for 

Model A340–500 and –600 series airplanes). 

FAA AD Differences 

Note 2: 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 MCAI European Aviation 

Safety Agency (EASA) Airworthiness 

Directive 2011–0073, dated April 20, 2011; 

Airbus AOT A330–26A3052, dated April 19, 

2011; Airbus AOT A340–200/300–26A4044, 

dated April 19, 2011; and Airbus AOT A340– 

500/600–26A5024, dated April 19, 2011; for 

related information. 

Material Incorporated by Reference 

(l) 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) of the 

following service information under 5 U.S.C. 

552(a) and 1 CFR part 51: 

(1) Airbus All Operators Telex (AOT) 

A330–26A3052, dated April 19, 2011. Only 

the first page of this document contains the 

document number and date. 

(2) Airbus AOT A340–200/300–26A4044, 

dated April 19, 2011. Only the first page of 

this document contains the document 

number and date. 

(3) Airbus AOT A340–500/600–26A5024, 

dated April 19, 2011. Only the first page of 

this document contains the document 

number and date. 

(4) 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. 

(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. 

(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 

December 6, 2011. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2011–32021 Filed 12–16–11; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2011–0199; Directorate 

Identifier 2011–CE–005–AD; Amendment 

39–16890; AD 2011–06–06 R1] 

RIN 2120–AA64 

Airworthiness Directives; Eclipse 

Aerospace, Inc. Airplanes Equipped 

With Pratt & Whitney Canada, Corp. 

PW610F–A Engines 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are revising an existing 

airworthiness directive (AD) that 

applies to all Eclipse Aerospace, Inc. 

Model EA500 airplanes equipped with 

Pratt & Whitney Canada, Corp. (P&WC) 

Model PW610F–A engines. The existing 

AD currently requires incorporating an 

operating limitation of a maximum 

operating altitude of 30,000 feet into 

Section 2, Limitations, of the airplane 

flight manual (AFM). Since we issued 

that AD, P&WC has developed a design 

change for the combustion chamber 

liner assembly. This new AD retains the 

requirements of the current AD, clarifies 

the engine applicability, and allows the 

option of incorporating the design 

change to terminate the current 

operating limitation and restore the 

original certificated maximum operating 

altitude of 41,000 feet. We are issuing 

this AD to correct the unsafe condition 

on these products. 

DATES: This AD is effective January 23, 

2012. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in the AD 

as of January 23, 2012. 

ADDRESSES: For service information 

identified in this AD, contact Pratt & 

Whitney Canada, 1000 Marie-Victorin 

Blvd., Longueuil, Quebec, J4G 1A1 

Canada; telephone: (800) 268–8000; 

Internet: www.P&WC.ca. You may 

review copies of the referenced service 

information at the FAA, Small Airplane 

Directorate, 901 Locust, Kansas City, 

Missouri 64106. For information on the 

availability of this material at the FAA, 

call (816) 329–4148. 


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