Federal Register / Vol. 78, No. 220 / Thursday, November 14, 2013 / Rules and Regulations 68347 

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 airworthiness 

directive (AD): 

2013–23–03 The Boeing Company: 

Amendment 39–17658; Docket No. 

FAA–2013–0871; Directorate Identifier 

2013–NM–187–AD. 

(a) Effective Date 

This AD is effective November 29, 2013. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to The Boeing Company 

Model 747–100, 747–100B, 747–100B SUD, 

747–200B, 747–200C, 747–200F, 747–300, 

747–400, 747–400D, 747–400F, and 747SR 

series airplanes, certificated in any category, 

as identified in Boeing Alert Service Bulletin 

747–57A2343, dated September 12, 2013. 

(d) Subject 

Joint Aircraft System Component (JASC)/

Air Transport Association (ATA) of America 

Code 57, Wings. 

(e) Unsafe Condition 

This AD was prompted by a report of the 

fracture of an inboard actuator attach fitting 

of the outboard flap. An inspection of the 

attach fitting revealed that it was incorrectly 

machined with a cylindrical profile instead 

of a conical profile, resulting in reduced wall 

thickness. We are issuing this AD to detect 

and correct defective inboard actuator attach 

fittings which, combined with loss of the 

outboard actuator load path, could result in 

uncontrolled retraction of the outboard flap, 

damage to flight control systems, and 

consequent reduced controllability of the 

airplane. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Part Number Inspection 

Within 90 days after the effective date of 

this AD: Inspect to determine the part 

number of the inboard actuator attach fittings 

of the outboard flaps, in accordance with Part 

1 of the Accomplishment Instructions of 

Boeing Alert Service Bulletin 747–57A2343, 

dated September 12, 2013. 

(h) Actions for Certain Attach Fittings 

If, during the inspection required by 

paragraph (g) of this AD, any inboard 

actuator attach fitting having part number 

(P/N) 65B08564–7 is found, before further 

flight, do the actions specified in paragraph 

(h)(1) or (h)(2) of this AD. 

(1) Do a detailed inspection of the inboard 

actuator attach fitting for a cylindrical defect, 

in accordance with Part 2 of the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin 747–57A2343, dated 

September 12, 2013. If any cylindrical defect 

is found, before further flight, do the actions 

specified in paragraph (h)(1)(i) or (h)(1)(ii) of 

this AD. 

(i) Do a minimum thickness inspection of 

the inboard actuator attach fitting to 

determine minimum wall thickness of the 

actuator fitting assembly, in accordance with 

Part 3 of the Accomplishment Instructions of 

Boeing Alert Service Bulletin 747–57A2343, 

dated September 12, 2013. If the minimum 

thickness of the wall is less than 0.130 inch: 

Before further flight, replace the inboard 

actuator attach fitting of the outboard flap, in 

accordance with Part 4 of the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin 747 57A2343, dated 

September 12, 2013. 

(ii) Replace the inboard actuator attach 

fitting of the outboard flap, in accordance 

with Part 4 of the Accomplishment 

Instructions of Boeing Alert Service Bulletin 

747–57A2343, dated September 12, 2013. 

(2) Replace the inboard actuator attach 

fitting of the outboard flap, in accordance 

with Part 4 of the Accomplishment 

Instructions of Boeing Alert Service Bulletin 

747–57A2343, dated September 12, 2013. 

(i) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Seattle 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 

paragraph (j) of this AD. Information may be 

emailed to: 9-ANM-Seattle-ACO-AMOCRequests@faa.gov. 

(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. 

(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 the 

Boeing Commercial Airplanes Organization 

Designation Authorization (ODA) that 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. 

(4) If the service information contains steps 

that are labeled as RC (Required for 

Compliance), those steps must be done to 

comply with this AD; any steps that are not 

labeled as RC are recommended. Those steps 

that are not labeled as RC may be deviated 

from, done as part of other actions, or done 

using accepted methods different from those 

identified in the specified service 

information without obtaining approval of an 

AMOC, provided the steps labeled as RC can 

be done and the airplane can be put back in 

a serviceable condition. Any substitutions or 

changes to steps labeled as RC require 

approval of an AMOC. 

(j) Related Information 

For more information about this AD, 

contact Nathan Weigand, Aerospace 

Engineer, Airframe Branch, ANM–120S, 

FAA, Seattle Aircraft Certification Office, 

1601 Lind Avenue SW., Renton, WA 98057– 

3356; phone: 425–917–6428; fax: 425–917– 

6590; email: nathan.p.weigand@faa.gov. 

(k) Material Incorporated by Reference 

(1) The Director of the Federal Register 

approved the incorporation by reference 

(IBR) of the service information listed in this 

paragraph under 5 U.S.C. 552(a) and 1 CFR 

part 51. 

(2) You must use this service information 

as applicable to do the actions required by 

this AD, unless the AD specifies otherwise. 

(i) Boeing Alert Service Bulletin 747– 

57A2343, dated September 12, 2013. 

(ii) Reserved. 

(3) For service information identified in 

this AD, contact Boeing Commercial 

Airplanes, Attention: Data & Services 

Management, P.O. Box 3707, MC 2H–65, 

Seattle, WA 98124–2207; telephone 206– 

544–5000, extension 1; fax 206–766–5680; 

Internet https://www.myboeingfleet.com. 

(4) You may review copies of the 

referenced 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. 

(5) You may view this 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/cfr/ibrlocations.html. 

Issued in Renton, Washington, on October 

31, 2013. 

Jeffrey E. Duven, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2013–27015 Filed 11–13–13; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2013–0329; Directorate 

Identifier 2012–NM–032–AD; Amendment 

39–17596; AD 2013–19–14] 

RIN 2120–AA64 

Airworthiness Directives; Airbus 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: We are superseding 

Airworthiness Directives (ADs) 2009– 

04–07 and 2011–02–09 for certain 


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68348 Federal Register / Vol. 78, No. 220 / Thursday, November 14, 2013 / Rules and Regulations 

Airbus Model A330–200, A330–200 

Freighter, A300–300, A340–200, A340– 

300, A340–500, and A340–600 series 

airplanes. AD 2009–04–07 required 

revising the airplane flight manual 

(AFM) to include appropriate 

operational procedures to prevent the 

air data inertial reference unit (ADIRU) 

from providing erroneous data to other 

airplane systems. AD 2011–02–09 

required revising the AFM to provide 

appropriate operational procedures to 

prevent the airplane flight directors 

(FDs), autopilot (AP), and auto-thrust reengagement in the event of airspeed 

sources providing similar but erroneous 

data. This new AD requires that 

operators modify or replace all three 

flight control primary computers 

(FCPCs) with new software standards. 

Since we issued ADs 2009–04–07 and 

2011–02–09, we have determined that 

new software standards for the FCPCs 

are necessary to inhibit autopilot reengagement under unreliable airspeed 

conditions. This new AD also removes 

certain airplanes from the applicability. 

We are issuing this AD to prevent 

autopilot engagement under unreliable 

airspeed conditions, which could result 

in reduced controllability of the 

airplane. 

DATES: This AD becomes effective 

December 19, 2013. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in this AD 

as of December 19, 2013. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain other publications listed in 

this AD as of February 9, 2011 (76 FR 

4219, January 25, 2011). 

The Director of the Federal Register 

approved the incorporation by reference 

of certain other publications listed in 

this AD as of March 5, 2009 (74 FR 

7549, February 18, 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 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. 

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 by adding an AD that would 

apply to the specified products. The 

NPRM was published in the Federal 

Register on April 16, 2013 (78 FR 

22432), and proposed to supersede AD 

2009–04–07, Amendment 39–15813 (74 

FR 7549, February 18, 2009); and AD 

2011–02–09, Amendment 39–16583 (76 

FR 4219, January 25, 2011). The NPRM 

proposed to correct an unsafe condition 

for the specified products. 

The European Aviation Safety Agency 

(EASA), which is the Technical Agent 

for the Member States of the European 

Community, has issued EASA AD 2011– 

0199R1, dated February 17, 2012 

(referred to after this as the Mandatory 

Continuing Airworthiness Information, 

or ‘‘the MCAI’’), to correct an unsafe 

condition for the specified products. 

The MCAI states: 

It has been determined that, when there are 

significant differences between all airspeed 

sources, the flight controls of an Airbus A330 

or A340 aeroplane will revert to alternate 

law, the autopilot (AP) and the auto-thrust 

(A/THR) automatically disconnect, and the 

Flight Directors (FD) bars are automatically 

removed. 

Further analyses have shown that, after 

such an event, if two airspeed sources 

become similar while still erroneous, the 

flight guidance computers will display the 

FD bars again, and enable the re-engagement 

of AP and A/THR. However, in some cases, 

the AP orders may be inappropriate, such as 

possible abrupt pitch command. 

In order to prevent such events which may, 

under specified circumstances, constitute an 

unsafe condition, EASA issued AD 2010– 

0271 [http://ad.easa.europa.eu/ad/2010- 

0271] [which corresponds to FAA AD 2011– 

02–09, Amendment 39–16583 (76 FR 4219, 

January 25, 2011)] to require an amendment 

of the Flight Manual to ensure that flight 

crews apply the appropriate operational 

procedure. 

Since that [EASA] AD was issued, new 

FCPC software standards have been 

developed that will inhibit autopilot 

engagement under unreliable airspeed 

conditions. 

Consequently, EASA issued AD 2011–0199 

to require software standard upgrade of the 

three FCPCs by either modification or 

replacement, as follows: 

—Software standard P11A/M20A on FCPC 

2K2 hardware for A330–200/–300 

aeroplanes [with electrical rudder], 

through Airbus Service Bulletin (SB) 

A330–27–3176, 

—software standard P12A/M21A on FCPC 

2K1 hardware and M21A on FCPC 2K0 

hardware for A330–200/–300 aeroplanes 

[with mechanical rudder], through Airbus 

SB A330–27–3177, 

—software standard L22A on FCPC 2K1 

hardware and L22A on FCPC 2K0 

hardware for A340–200/–300 aeroplanes 

[with mechanical rudder], through Airbus 

SB A340–27–4174, and 

— software standard L21A on FCPC 2K2 

hardware for A340–300 aeroplanes [with 

electrical rudder], through Airbus SB 

A340–27–4162. 

* * * * * 

EASA has also issued MCAI 2013– 

0107, dated May 17, 2013, which states: 

An A330 aeroplane experienced a sudden 

nose down movement while in cruise. This 

event was preceded by an automatic 

autopilot disconnection, which triggered the 

‘‘NAV IR1 FAULT’’ Electronic Centralised 

Aircraft Monitor (ECAM) Caution. 

Investigation results highlighted that at the 

time of the event, the Air Data Reference 1 

(ADR) part of ADIRU1 was providing 

erroneous and temporary wrong parameters 

in a random manner. This abnormal behavior 

of the ADR1 led to several consequences 

such as unjustified stall and over speed 

warnings, loss of attitude information on 

Captain Primary Flight Display (PFD) and 

several ECAM warnings. Among the 

abnormal parameters, the provided Angle of 

Attack (AoA) value was such that the flight 

control computers commanded the sudden 

nose down movement. 

Further investigation results concluded 

that this event was caused by erroneous and 

undetected AoA values (spikes) generated by 

the ADIRU1. 

This condition, if not corrected, could lead 

to further similar occurrences, possibly 

resulting in loss of control of the aeroplane. 

To address this potential unsafe condition 

and as an interim solution, EASA issued 

Emergency AD 2009–0012–E [http://

ad.easa.europa.eu/ad/2009-0012-E] to 

require implementation of an aircraft Flight 

Manual (AFM) operational procedure, to 

isolate both the Inertial Reference (IR) and 

ADR in case a faulty IR is detected. 

Since that [EASA] AD was issued, a final 

fix solution was developed, consisting of new 

FCPC software standards, which prevents the 

potential unsafe condition and cancels the 

AFM operational procedure required by 

EASA AD 2009–0012–E. Consequently, 

EASA issued AD 2011–0199R1 to require this 

software standard upgrade of the three FCPCs 

by either modification or replacement, for 

A330 and A340–200/–300 aeroplanes. 

Due to similar design, Airbus A340–500/– 

600 aeroplanes are also impacted by this 

issue, and Airbus developed Service Bulletin 

(SB) A340–27–5051 which gives instructions 

for a software standard upgrade of the three 

FCPCs, irrespective of ADIRU manufacturer. 

For the reasons described above, this AD 

requires a software standard upgrade of the 

three FCPCs for A340–500/–600 aeroplanes, 

which cancels the operational procedure 

imposed by EASA AD 2009–0012–E. 

You may obtain further information by 

examining the MCAI in the AD docket 

on the Internet at http://

www.regulations.gov/


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Federal Register / Vol. 78, No. 220 / Thursday, November 14, 2013 / Rules and Regulations 68349 

#!documentDetail;D=FAA-2013-0329- 

0003. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. We 

considered the comments received. 

Support for the NPRM (78 FR 22432, 

April 16, 2013) 

The Air Line Pilots Association 

International supported the intent of the 

NPRM (78 FR 22432, April 16, 2013). 

Michael Carrera agreed with the 

requirements of the NPRM (78 FR 

22432, April 16, 2013). 

Request To Include EASA AD 2013– 

0107, Dated May 17, 2013, in the NPRM 

(78 FR 22432, April 16, 2013) 

Airbus stated that EASA has issued 

AD 2013–0107, issued May 17, 2013, 

and requested that we include the 

equivalent actions in this AD. Airbus 

stated that the requirements of EASA 

AD 2013–0107 are for Model A340–500 

and –600 airplanes and are equivalent to 

the requirements of this AD for Model 

A330 and A340–200 and –300 airplanes. 

Airbus stated that the actions required 

by EASA AD 2013–0107 enables a 

supersedure action required by FAA AD 

2009–04–07, Amendment 39–15813 (74 

FR 7549, February 18, 2009). Airbus 

also stated that for Model A340–541 and 

A340–642 airplanes, the actions 

required by EASA AD 2013–0107 

terminate the requirements of paragraph 

(g) of the NPRM (78 FR 22432, April 16, 

2013) and AD 2009–04–07. 

We agree that EASA AD 2013–0107 

mandates similar actions for Model 

A340–541 and A340–642 airplanes and 

eliminates the same revisions of the 

AFM as mandated by FAA AD 2009– 

04–07, Amendment 39–15813 (74 FR 

7549, February 18, 2009). Although 

there are no Model A340–541 or A340– 

642 airplanes currently registered in the 

U.S., we have included the 

requirements of EASA AD 2013–0107 

(which specifies to modify or replace 

certain FCPCs in accordance with 

Airbus Service Bulletin A340–27–5051) 

in this final rule, and have added Model 

A340–541 and A340–642 airplanes to 

paragraph (c)(2) of this final rule. We 

have also added new paragraph (j) to 

this final rule to include actions 

specified in Airbus Mandatory Service 

Bulletin A340–27–5051, dated July 16, 

2012, for Model A340–541 and A340– 

642 series airplanes. Subsequent 

paragraphs have been redesignated 

accordingly. In addition, we have 

clarified paragraphs (i)(3) and (i)(4) of 

this final rule to state that the actions 

specified in paragraphs (i)(3) and (i)(4) 

of this final rule apply to Model A340– 

200 and –300 series airplanes. 

Request To Include the Equivalent 

Mandatory Actions of EASA AD 2012– 

0271, Dated December 21, 2012, in the 

NPRM (78 FR 22432, April 16, 2013) 

Airbus stated that EASA has issued 

AD 2012–0271, dated December 21, 

2012, on the same subject and requested 

that the equivalent mandatory actions 

be included in this AD. EASA AD 2012– 

0271 requires installation of the FCPC 

multi role transport tanker (MRTT2) 

standard applicable to Model A330 

airplanes on which Airbus Service 

Bulletin A330–27–3156 has been 

embodied. Airbus stated that this 

requirement for Model A330 MRTT 

airplanes is equivalent to one in the 

NPRM (78 FR 22432, April 16, 2013) for 

other Model A330 airplanes. The 

commenter stated that this action 

enables the supersedure of the actions 

required by FAA AD 2009–04–07, 

Amendment 39–15813 (74 FR 7549, 

February 18, 2009); and AD 2011–02– 

09, Amendment 39–16583 (76 FR 4219, 

January 25, 2011); and terminates the 

requirements of paragraphs (g) and (h) 

of the NPRM (78 FR 22432, April 16, 

2013). 

We disagree with including the 

requested actions in this final rule. 

EASA AD 2012–0271, issued December 

21, 2012, requires modification or 

replacement of the three FCPCs to 

install software standard MRTT2 on 

Model A330–200 airplanes with 

commercial designation MRTT. We 

have not type-validated Model A330– 

200 MRTT airplanes and that model is 

not on the FAA type certificate data 

sheet. We have not taken actions in 

regard to EASA AD 2012–0271 related 

to Model A330–200 MRTT airplanes for 

that reason. No change has been made 

to this final rule in this regard. 

Request To Update AFM Temporary 

Revision (TR) References 

Airbus requested that we update the 

references for the AFM TRs. Airbus 

stated that the references for the AFM 

TRs have been changed. 

We disagree with changing the 

references for the AFM TRs in this final 

rule. The new designation of the AFM 

TRs was introduced after the 

publication of AD 2009–04–07, 

Amendment 39–15813 (74 FR 7549, 

February 18, 2009). Changing the 

references could cause 

misunderstanding or confusion. No 

change has been made to this final rule 

in this regard. 

Conclusion 

We reviewed the available data, 

including the comments received, and 

determined that air safety and the 

public interest require adopting this AD 

with the changes described previously 

and minor editorial changes. We have 

determined that these changes: 

• Are consistent with the intent that 

was proposed in the NPRM (78 FR 

22432, April 16, 2013) for correcting the 

unsafe condition; and 

• Do not add any additional burden 

upon the public than was already 

proposed in the NPRM (78 FR 22432, 

April 16, 2013). 

Related AD 

Accomplishing the actions specified 

in paragraphs (i)(1) through (i)(4) of this 

final rule is compliant with the optional 

actions specified in paragraphs (l) and 

(o)(1) through (o)(4) of AD 2013–05–08, 

Amendment 39–17380 (78 FR 27015, 

May 9, 2013). 

Costs of Compliance 

We estimate that this AD affects about 

59 products of U.S. registry. 

The actions that are required by AD 

2009–04–07, Amendment 39–15813 (74 

FR 7549, February 18, 2009), and 

retained in this AD take about 1 workhour per product, at an average labor 

rate of $85 per work hour. Required 

parts cost about $0 per product. Based 

on these figures, the estimated cost of 

the actions that were required by AD 

2009–04–07 is $85 per product. 

The actions that are required by AD 

2011–02–09, Amendment 39–16583 (76 

FR 4219, January 25, 2011), and retained 

in this AD take about 1 work-hour per 

product, at an average labor rate of $85 

per work hour. Required parts cost 

about $0 per product. Based on these 

figures, the estimated cost of the actions 

currently required by AD 2011–02–09 is 

$85 per product. 

We estimate that it takes about 5 

work-hours per product to comply with 

the new basic requirements of this AD. 

The average labor rate is $85 per workhour. Required parts would cost about 

$0 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 on U.S. operators to be $25,075, 

or $425 per product. 

Authority for This Rulemaking 

Title 49 of the United States Code 

specifies the FAA’s authority to issue 


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68350 Federal Register / Vol. 78, No. 220 / Thursday, November 14, 2013 / Rules and Regulations 

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 that 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); 

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. 

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/

#!docketDetail;D=FAA-2013-0329; 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 

MCAI, 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. 

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: 

■ (a) Removing airworthiness directive 

(AD) 2009–04–07, Amendment 39– 

15813 (74 FR 7549, February 18, 2009), 

and AD 2011–02–09, Amendment 39– 

16583 (76 FR 4219, January 25, 2011); 

and 

■ (b) Adding the following new AD: 

2013–19–14 Airbus: Amendment 39–17596. 

Docket No. FAA–2013–0329; Directorate 

Identifier 2012–NM–032–AD. 

(a) Effective Date 

This airworthiness directive (AD) becomes 

effective December 19, 2013. 

(b) Affected ADs 

This AD supersedes AD 2009–04–07, 

Amendment 39–15813 (74 FR 7549, February 

18, 2009); and AD 2011–02–09, Amendment 

39–16583 (76 FR 4219, January 25, 2011). 

(c) Applicability 

This AD applies to the Airbus airplanes, 

certificated in any category, as identified in 

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

(1) Model A330–223F, –243F, –201, –202, 

–203, –223, –243, –301, –302, –303, –321, 

–322, –323, –341, –342, and –343 airplanes; 

except those on which Airbus Modification 

201654 has been embodied in production, or 

Airbus Service Bulletin A330–27–3156 has 

been incorporated in service. 

(2) All Model A340–211, –212, –213, –311, 

–312, –313, –541, and 642 airplanes. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 27, Flight controls. 

(e) Reason 

This AD was prompted by the possibility 

that, due to significant differences among all 

airspeed sources, the flight controls will 

revert to alternate law, the autopilot (AP) and 

the auto-thrust (A/THR) automatically 

disconnect, and the flight director (FD) bars 

are automatically removed. Then, if two 

airspeed sources become similar while still 

erroneous, the flight guidance computers will 

display the FD bars again, and enable the reengagement of the AP and A/THR. In some 

cases, however, the AP orders may be 

inappropriate, such as possible abrupt pitch 

command. We are issuing this AD to prevent 

autopilot engagement under unreliable 

airspeed conditions, which could result in 

reduced controllability of the airplane. 

(f) Compliance 

You are responsible for having the actions 

required by this AD performed within the 

compliance times specified, unless the 

actions have already been done. 

(g) Retained Airplane Flight Manual (AFM) 

Revision: Certain NAV Faults or ATT Flag 

on PFD 

This paragraph restates the actions 

required by paragraph (f) of AD 2009–04–07, 

Amendment 39–15813 (74 FR 7549, February 

18, 2009). For all airplanes except Model 

A330–223F and –243F airplanes: Within 14 

days after March 5, 2009 (the effective date 

of AD 2009–04–07), revise the applicable 

section of the A330 or A340 (Airbus) Flight 

Manual (FM) by inserting a copy of A330 

(Airbus) Temporary Revision (TR) 4.02.00/

46, or A340 (Airbus) TR 4.02.00/54, both 

Issue 3, both dated January 13, 2009, as 

applicable. Thereafter, operate the airplane 

according to the limitations and procedures 

in the TRs. When information identical to 

that in the TR has been included in the 

general revisions of the FM, the general 

revisions may be inserted in the FM, and the 

TR may be removed. 

(h) Retained AFM Revision: Alternate Law 

Associated With AP and A/THR 

Disconnection 

This paragraph restates the actions 

required by paragraph (g) of AD 2011–02–09, 

Amendment 39–16583 (76 FR 4219, January 

25, 2011). Within 15 days after February 9, 

2011 (the effective date of AD 2011–02–09), 

do the actions in paragraph (h)(1) or (h)(2) of 

this AD. 

(1) Revise the Limitations and Abnormal 

Sections of the Airbus A330/A340 AFM to 

include the following statement and operate 

the airplane according to these limitations 

and procedures. This may be done by 

inserting a copy of this AD in the AFM. 

When a statement identical to that in figure 

1 to paragraph (h)(1) of this AD has been 

included in the general revisions of the 

Limitations and Abnormal Sections of the 

AFM, the general revisions may be inserted 

into the AFM, and the copy of this AD may 

be removed from the AFM. 

BILLING CODE 4910–13–P 


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BILLING CODE 4910–13–C 

(2) Revise the Limitations and Abnormal 

Sections of the Airbus A330/A340 AFM to 

include the information in Airbus A330/

A340 TR TR149 (for Model A330 airplanes) 

or TR TR150 (for Model A340–200 and -300 

series airplanes), both Issue 1.0, both dated 

December 20, 2010. These TRs introduce 

procedures for operation of the auto pilot and 

auto-thrust disconnect. Operate the airplane 

according to the limitations and procedures 

in the TRs. This may be done by inserting 

copies of Airbus A330/A340 TR TR149 or 

TR150, both Issue 1.0, both dated December 

20, 2010; as applicable; into the Airbus 

A330/A340 AFM. When these TRs have been 

included in general revisions of the AFM, the 

general revisions may be inserted in the 

AFM, and the TRs may be removed. 

(i) New Software Standard Upgrade for 

Model A330 Series Airplanes, and Model 

A340–200 and –300 Series Airplanes 

Within 10 months after the effective date 

of this AD, upgrade (by modification or 

replacement, as applicable) the three flight 

control primary computers (FCPCs), as 

specified in paragraphs (i)(1), (i)(2), (i)(3), 

and (i)(4) of this AD, as applicable. 

Accomplishment of the applicable 

requirements of this paragraph terminates the 

requirements of paragraphs (g) and (h) of this 

AD. Accomplishing the actions specified in 

paragraphs (i)(1) through (i)(4) of this AD are 

compliant with the optional actions specified 

in paragraphs (l) and (o)(1) through (o)(4) of 

AD 2013–05–08, Amendment 39–17380 (78 

FR 27015, May 9, 2013). 

(1) For Model A330 series airplanes: 

Upgrade to software standard P11A/M20A on 

FCPC 2K2 hardware, in accordance with the 

Accomplishment Instructions of Airbus 

Mandatory Service Bulletin A330–27–3176, 

Revision 02, dated April 24, 2012. 

(2) For Model A330 series airplanes: 

Upgrade to software standard P12A/M21A on 

FCPC 2K1 hardware, and software standard 

M21A on FCPC 2K0 hardware, in accordance 

with the Accomplishment Instructions of 

Airbus Mandatory Service Bulletin A330–27– 

3177, dated December 21, 2011. 

(3) For Model A340–200 and –300 series 

airplanes: Upgrade to software standard 

L22A on FCPC 2K1 hardware, and software 

standard L22A on FCPC 2K0 hardware, in 

accordance with the Accomplishment 

Instructions of Airbus Mandatory Service 

Bulletin A340–27–4174, dated November 21, 

2011. 

(4) For Model A340–200 and –300 series 

airplanes: Upgrade to software standard 

L21A on FCPC 2K2 hardware, in accordance 

with the Accomplishment Instructions of 

Airbus Mandatory Service Bulletin A340–27– 

4162, Revision 01, dated September 17, 2012. 

(j) New Software Standard Upgrade for 

Model A340–541 and –642 Series Airplanes 

(1) Within 10 months after the effective 

date of this AD, modify or replace the three 

FCPCs to integrate software standard W12 on 

FCPC 2K2 hardware, in accordance with the 

Accomplishment Instructions of Airbus 

Mandatory Service Bulletin A340–27–5051, 

dated July 16, 2012. Accomplishment of the 

applicable requirements of this paragraph 

terminates the requirements of paragraphs (g) 

and (h) of this AD. 

(2) After accomplishing the modification in 

accordance with paragraph (j)(1) of this AD, 

do not install an FCPC on the airplane unless 

the FCPC is 2K2 hardware with integrating 

software standard W12. 

(k) Credit for Previous Actions 

(1) This paragraph provides credit for the 

actions specified in paragraph (i)(1) of this 

AD, if those actions were performed before 

the effective date of this AD using Airbus 

Mandatory Service Bulletin A330–27–3176, 

dated July 26, 2011; or Airbus Mandatory 

Service Bulletin A330–27–3176, Revision 01, 

dated March 27, 2012; which are not 

incorporated by reference in this AD. 

(2) This paragraph provides credit for the 

actions specified in paragraph (i)(4) of this 

AD, if those actions were performed before 

the effective date of this AD using Airbus 


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Mandatory Service Bulletin A340–27–4162, 

dated January 10, 2012, which is not 

incorporated by reference in this AD. 

(l) Other FAA AD Provisions 

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. 

(m) Related Information 

(1) Refer to Mandatory Continuing 

Airworthiness Information (MCAI) European 

Aviation Safety Agency Airworthiness 

Directives 2011–0199R1, dated February 17, 

2012; and 2013–0107, dated May 17, 2013; 

for related information. The MCAI can be 

found in the AD docket on the Internet at 

http://www.regulations.gov/

#!documentDetail;D=FAA–2013–0329–0003. 

(2) Service information that is referenced 

in this AD that is not incorporated by 

reference in this AD may be viewed at the 

addresses identified in paragraphs (n)(6) and 

(n)(7) of this AD. 

(n) Material Incorporated by Reference 

(1) The Director of the Federal Register 

approved the incorporation by reference 

(IBR) of the service information listed in this 

paragraph under 5 U.S.C. 552(a) and 1 CFR 

part 51. 

(2) You must use this service information 

as applicable to do the actions required by 

this AD, unless this AD specifies otherwise. 

(3) The following service information was 

approved for IBR on December 19, 2013. 

(i) Airbus Mandatory Service Bulletin 

A330–27–3176, Revision 02, dated April 24, 

2012. 

(ii) Airbus Mandatory Service Bulletin 

A330–27–3177, dated December 21, 2011. 

(iii) Airbus Mandatory Service Bulletin 

A340–27–4162, Revision 01, dated 

September 17, 2012. 

(iv) Airbus Mandatory Service Bulletin 

A340–27–4174, dated November 21, 2011. 

(v) Airbus Mandatory Service Bulletin 

A340–27–5051, dated July 16, 2012. 

(4) The following service information was 

approved for IBR on February 9, 2011 (76 FR 

4219, January 25, 2011). 

(i) Airbus A330/A340 Temporary Revision 

TR149, Issue 1.0, dated December 20, 2010, 

to the Airbus A330/A340 Airplane Flight 

Manual. 

(ii) Airbus A330/A340 Temporary Revision 

TR150, Issue 1.0, dated December 20, 2010, 

to the Airbus A330/A340 Airplane Flight 

Manual. 

(5) The following service information was 

approved for IBR on March 5, 2009 (74 FR 

7549, February 18, 2009). 

(i) Airbus A330 Temporary Revision 

4.02.00/46, Issue 3, dated January 13, 2009, 

to the Airbus A330 Airplane Flight Manual. 

(ii) Airbus A340 Temporary Revision 

4.02.00/54, Issue 3, dated January 13, 2009, 

to the Airbus A340 Airplane Flight Manual. 

(6) 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. 

(7) You may view copies of the service 

information at the FAA, Transport Airplane 

Directorate, 1601 Lind Avenue SW., Renton, 

WA. For information on the availability of 

this material at the FAA, call 425–227–1221. 

(8) You may view this 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/cfr/ibrlocations.html. 

Issued in Renton, Washington, on 

September 13, 2013. 

Jeffrey E. Duven, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2013–26565 Filed 11–13–13; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2013–0212; Directorate 

Identifier 2012–NM–116–AD; Amendment 

39–17509; AD 2013–14–04] 

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 all 

Airbus Model A330–223F, –223, –321, 

–322, and –323 airplanes. This AD was 

prompted by fatigue load analysis that 

determined that the inspection interval 

for certain pylon bolts must be reduced. 

This AD requires a torque check of 

forward engine mount bolts, and 

replacement if necessary. We are issuing 

this AD to detect and correct loose or 

broken bolts, which could lead to 

engine detachment in-flight, and 

damage to the airplane. 

DATES: This AD becomes effective 

December 19, 2013. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of December 19, 2013. 

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 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. 

FOR FURTHER INFORMATION CONTACT: 

Vladimir Ulyanov, Aerospace Engineer, 

International Branch, ANM–116, 

Transport Airplane Directorate, FAA 

1601 Lind Avenue SW., Renton, WA 

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 by adding an AD that would 

apply to the specified products. The 

NPRM was published in the Federal 

Register on March 28, 2013 (78 FR 

18925). The NPRM proposed to correct 

an unsafe condition for the specified 

products. 

The European Aviation Safety Agency 

(EASA), which is the Technical Agent 

for the Member States of the European 

Community, has issued EASA 

Airworthiness Directive 2012–0094, 

dated May 31, 2012 (referred to after 

this as the Mandatory Continuing 

Airworthiness Information, or ‘‘the 

MCAI’’), to correct an unsafe condition 

for the specified products. The MCAI 

states: 

The forward mount engine pylon bolts, 

Part Number (P/N) 51U615, fitted on Airbus 

A330 aeroplanes with Pratt & Whitney (PW) 


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