9398 Federal Register / Vol. 79, No. 33 / Wednesday, February 19, 2014 / Rules and Regulations 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2013–0791; Directorate 

Identifier 2012–NM–026–AD; Amendment 

39–17745; AD 2014–03–08] 

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 A318, A319, A320, and 

A321 series airplanes. This AD was 

prompted by a report that an 

investigation showed that when a 

certain combination of a target/

proximity sensor serial number is 

installed on a flap interconnecting strut, 

a ‘‘target FAR’’ signal cannot be detected 

when it reaches the mechanical end 

stop of the interconnecting strut. This 

AD requires an inspection to determine 

the part number of the interconnecting 

struts installed on the wings, identifying 

the part number and the serial number 

of the associated target and proximity 

sensor if applicable, and replacing or reidentifying the flap interconnecting 

strut if applicable. We are issuing this 

AD to detect and correct a latent failure 

of the flap down drive disconnection 

due to an already-failed interconnecting 

strut sensor, which could result in 

asymmetric flap panel movement and 

consequent loss of control of the 

airplane. 

DATES: This AD becomes effective 

March 26, 2014. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of March 26, 2014. 

ADDRESSES: You may examine the AD 

docket on the Internet at http://

www.regulations.gov/

#!docketDetail;D=FAA-2013-0791; or in 

person at the Docket Management 

Facility, 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, Airworthiness 

Office—EAS, 1 Rond Point Maurice 

Bellonte, 31707 Blagnac Cedex, France; 

telephone +33 5 61 93 36 96; fax +33 5 

61 93 44 51; email account.airwortheas@airbus.com; Internet http://

www.airbus.com. You may view this 

referenced 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. 

FOR FURTHER INFORMATION CONTACT: 

Sanjay Ralhan, Aerospace Engineer, 

International Branch, ANM 116, 

Transport Airplane Directorate, FAA, 

1601 Lind Avenue SW., Renton, WA 

98057–3356; telephone (425) 227–1405; 

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 all Airbus Model A318, A319, 

A320, and A321 series airplanes. The 

NPRM published in the Federal 

Register on September 25, 2013 (78 FR 

58975). The NPRM was prompted by a 

report that an investigation showed that 

when a certain combination of a target/ 

proximity sensor serial number is 

installed on a flap interconnecting strut, 

a ‘‘target FAR’’ signal cannot be detected 

when it reaches the mechanical end 

stop of the interconnecting strut. The 

NPRM proposed to require an 

inspection to determine the part number 

of the interconnecting struts installed on 

the wings, identifying the part number 

and the serial number of the associated 

target and proximity sensor if 

applicable, and replacing or reidentifying the flap interconnecting 

strut if applicable. We are issuing this 

AD to detect and correct a latent failure 

of the flap down drive disconnection 

due to an already-failed interconnecting 

strut sensor, which could result in 

asymmetric flap panel movement and 

consequent loss of control of the 

airplane. 

The European Aviation Safety Agency 

(EASA), which is the Technical Agent 

for the Member States of the European 

Community, has issued EASA 

Airworthiness Directive 2012–0012, 

dated January 23, 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 flap interconnecting strut is a safety 

device of the High Lift System which acts as 

an alternative load path from one flap surface 

to another in case of a flap drive system 

disconnection. In such a failure case, the 

installed proximity provide information to 

the slat flap control computer (SFCC) and the 

operation of the flap drive system is 

inhibited. 

A recent engineering investigation has 

shown that, when a certain combination of 

target/sensor serial number (s/n) is installed 

on a flap interconnecting strut, a ‘‘target 

FAR’’ signal cannot be detected when 

reaching the mechanical end stop of the 

interconnecting strut. 

This condition, if not corrected, could 

cause a flap down drive disconnection to 

remain undetected, due to an already-failed 

interconnecting strut sensor, potentially 

resulting in asymmetric flap panel movement 

and consequent loss of control of the 

aeroplane. 

For the reason described above, this 

[EASA] AD requires the identification and 

replacement [or re-identifying] of struts that 

have a certain target/sensor s/n combination 

installed. 

You may examine the MCAI in the 

AD docket on the Internet at http://

www.regulations.gov/#!documentDetail;

D=FAA-2013-0791-0002. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. We 

received no comments on the NPRM (78 

FR 58975, September 25, 2013) 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 this AD 

as proposed. We have determined that 

these minor changes: 

• Are consistent with the intent that 

was proposed in the NPRM (78 FR 

58975, September 25, 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 58975, 

September 25, 2013). 

Costs of Compliance 

We estimate that this AD affects 755 

airplanes of U.S. registry. 

We estimate the following costs to 

comply with this AD: 


ehiers on DSK2VPTVN1PROD with RULES
Federal Register / Vol. 79, No. 33 / Wednesday, February 19, 2014 / Rules and Regulations 9399 

ESTIMATED COSTS

Action Labor cost Parts cost Cost per 

product 

Cost on 

U.S. 

operators 

Inspection and Re-identification ... 8 work-hours × $85 per hour = $680 per inspection cycle ............... $0 $680 $513,400 

We estimate the following costs to do 

any necessary replacements that would 

be required based on the results of the 

inspection. We have no way of 

determining the number of aircraft that 

might need these replacements: 

ON-CONDITION COSTS

Action Labor cost Parts cost Cost per 

product 

Replacement ...................................... 10 work-hours × $85 per hour = $850 ........................................................... $0 $850 

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 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. 

Examining the AD Docket 

You may examine the AD docket on 

the Internet at http://

www.regulations.gov/

#!docketDetail;D=FAA-2013-0791; or in 

person at the Docket Management 

Facility 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. 

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: 

2014–03–08 Airbus: Amendment 39–17745. 

Docket No. FAA–2013–0791; Directorate 

Identifier 2012–NM–026–AD. 

(a) Effective Date 

This airworthiness directive (AD) becomes 

effective March 26, 2014. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to all Airbus Model A318– 

111, –112, –121, and –122 airplanes; Model 

A319–111, –112, –113, –114, –115, –131, 

–132, and –133 airplanes; Model A320–111, 

–211, –212, –214, –231, –232, and –233 

airplanes; and Model A321–111, –112, –131, 

–211, –212, –213, –231, and –232 airplanes; 

certificated in any category; all manufacturer 

serial numbers. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 27, Flight controls. 

(e) Reason 

This AD was prompted by a report that an 

investigation showed that when a certain 

combination of a target/proximity sensor 

serial number is installed on a flap 

interconnecting strut, a ‘‘target FAR’’ signal 

cannot be detected when reaching the 

mechanical end stop of the interconnecting 

strut. We are issuing this AD to detect and 

correct a latent failure of the flap down drive 

disconnection due to an already-failed 

interconnecting strut sensor, which could 

result in asymmetric flap panel movement 

and consequent loss of control 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) Inspection To Determine the Part Number 

of the Interconnecting Struts 

Within 8,000 flight hours after the effective 

date of this AD, inspect to determine the part 

number of the interconnecting struts 

installed on both the left-hand (LH) and 

right-hand (RH) wings of the airplane, in 

accordance with the Accomplishment 

Instructions of Airbus Service Bulletin A320– 

27–1206, Revision 01, dated October 10, 

2011. A review of the airplane maintenance 

records is acceptable for determining the part 

number of the installed interconnecting 

struts, in lieu of the inspection, if the part 

number of the installed interconnecting 

struts, and the part number and the serial 

number of the associated target and 

proximity sensor, can be conclusively 

determined from that review. 

(1) Airplanes on which Airbus 

Modification 27956 has been embodied in 


ehiers on DSK2VPTVN1PROD with RULES
9400 Federal Register / Vol. 79, No. 33 / Wednesday, February 19, 2014 / Rules and Regulations 

production, and on which no interconnecting 

strut has been replaced with a strut having 

a part number specified in figure 1 to 

paragraph (g) of this AD since the airplane’s 

first flight: No further work is required by 

paragraph (g) of this AD. 

(2) If, during the inspection required by 

paragraph (g) of this AD, any interconnecting 

strut is installed with a part number specified 

in figure 1 to paragraph (g) of this AD: Within 

8,000 flight hours after the effective date of 

this AD, determine the part number and the 

serial number of the associated target and 

proximity sensor. 

FIGURE 1 TO PARAGRAPH (G) OF THIS

AD—INTERCONNECTING STRUT

PART NUMBERS

Interconnecting strut part numbers 

D5757030500000 

D5757030500100 

D5757030500200 

D5757030500600 

D5757030500800 

D5757030501000 

D5757030501200 

D5757032200000 

(i) For airplanes having conditions 

specified in paragraphs (g)(2)(i)(A), 

(g)(2)(i)(B), (g)(2)(i)(C), and (g)(2)(i)(D) of this 

AD: Before further flight, replace the 

interconnecting strut with a serviceable unit, 

in accordance with the Accomplishment 

Instructions of Airbus Service Bulletin A320– 

27–1206, Revision 01, dated October 10, 

2011. For the purposes of this AD, a 

serviceable interconnecting strut is a unit 

which has been determined to be in 

compliance with the following requirements 

of this AD: 

(A) A target part number (P/N) ABS0121– 

13 or P/N 8–536–01; and 

(B) A target serial number lower than 1600, 

or a target serial number that is unreadable; 

and 

(C) A proximity sensor having P/N 

ABS0121–31 or P/N 8–372–04; and 

(D) A proximity sensor having a serial 

number between C59198 and C59435, or a 

serial number (S/N) C500000 or higher. 

(ii) For a target having S/N 1600 or higher 

and target P/N ABS0121–13 or P/N 8–536– 

01: Within 8,000 flight hours after the 

effective date of this AD, re-identify the 

interconnecting strut, in accordance with the 

Accomplishment Instructions of Airbus 

Service Bulletin A320–27–1206, Revision 01, 

dated October 10, 2011. 

(h) Parts Installation Prohibition 

As of the effective date of this AD, no 

person may install an interconnecting strut 

with a part number specified in figure 1 to 

paragraph (g) of this AD, on any airplane, 

except for parts identified in paragraph 

(g)(2)(ii) of this AD, provided that the actions 

in paragraph (g)(2)(ii) are done. 

(i) Credit for Previous Actions 

This paragraph provides credit for the 

actions required by paragraph (g) of this AD, 

if those actions were performed before the 

effective date of this AD using Airbus Service 

Bulletin A320–27–1206, dated January 28, 

2011, and if additional work has been 

accomplished using Airbus Service Bulletin 

A320–27–1206, Revision 01, dated October 

10, 2011. Airbus Service Bulletin A320–27– 

1206, dated January 28, 2011, is not 

incorporated by reference in this AD. 

(j) 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: 

Sanjay Ralhan, Aerospace Engineer, 

International Branch, ANM–116, Transport 

Airplane Directorate, FAA, 1601 Lind 

Avenue SW., Renton, Washington 98057– 

3356; telephone (425) 227–1405; 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. 

(k) Related Information 

(1) Refer to Mandatory Continuing 

Airworthiness Information (MCAI) EASA 

Airworthiness Directive 2012–0012, dated 

January 23, 2012, for related information. 

This MCAI may be found in the AD docket 

on the Internet at http://

www.regulations.gov/

#!documentDetail;D=FAA-2013-0791-0002. 

(2) Service information identified in this 

AD that is not incorporated by reference may 

be viewed at the addresses specified in 

paragraphs (l)(3) and (l)(4) of this AD. 

(l) 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. 

(i) Airbus Service Bulletin A320–27–1206, 

Revision 01, dated October 10, 2011. 

(ii) Reserved. 

(3) For service information identified in 

this AD, contact Airbus, Airworthiness 

Office—EAS, 1 Rond Point Maurice Bellonte, 

31707 Blagnac Cedex, France; telephone +33 

5 61 93 36 96; fax +33 5 61 93 44 51; email 

account.airworth-eas@airbus.com; Internet 

http://www.airbus.com. 

(4) You may view this 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. 

(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/ibr-locations.html. 

Issued in Renton, Washington, on January 

22, 2014. 

Jeffrey E. Duven, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2014–02996 Filed 2–18–14; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2013–0735; Directorate 

Identifier 2013–SW–014–AD; Amendment 

39–17748; AD 2014–03–11] 

RIN 2120–AA64 

Airworthiness Directives; Bell 

Helicopter Textron, Inc. (Bell) 

Helicopters 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for Bell 

Model 204B helicopters with a certain 

cable assembly installed. This AD 

requires inspecting the tail rotor (T/R) 

cable assembly for an incorrectly 

machined body. This AD is prompted 

by a report from Bell that a defective 

body on the cable prevents the barrel 

assembly from fully engaging in the 

body cavity. These actions are intended 

to prevent disengagement of the cable 

from the barrel, failure of the T/R pitch 

control, and subsequent loss of control 

of the helicopter. 

DATES: This AD is effective March 26, 

2014. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain document listed in this AD 

as of March 26, 2014. 

ADDRESSES: For service information 

identified in this AD, contact Bell 

Helicopter Textron, Inc., P.O. Box 482, 

Fort Worth, TX 76101; telephone (817) 

280–3391; fax (817) 280–6466; or at 

http://www.bellcustomer.com/files/. 

You may review a copy of the 


ehiers on DSK2VPTVN1PROD with RULES