Federal Register / Vol. 80, No. 142 / Friday, July 24, 2015 / Rules and Regulations 43925 

(3) Where Boeing Alert Service Bulletin 

737–53A1108, Revision 7, dated July 7, 2014, 

specifies accomplishment of a preventative 

modification in accordance with ‘‘Revision 6 

of this service bulletin,’’ this AD requires 

accomplishment of those actions to be done 

in accordance with Boeing Alert Service 

Bulletin 737–53A1108, Revision 7, dated July 

7, 2014. 

(4) Where table 4 in paragraph 1.E, 

‘‘Compliance,’’ of Boeing Alert Service 

Bulletin 737–53A1108, Revision 7, dated July 

7, 2014, specifies repairing a condition 

identified as any crack found in ‘‘an 

intercostal,’’ this AD requires repairing a 

condition identified as any crack found in 

‘‘an intercostal or attaching stringers.’’ 

(l) Credit for Previous Actions 

This paragraph provides credit for the 

actions required by paragraphs (g) and (h) of 

this AD, if those actions were performed 

before the effective date of this AD using 

Boeing Alert Service Bulletin 737–53A1108, 

Revision 6, dated January 9, 2014. This 

service information is not incorporated by 

reference in this AD. 

(m) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Los Angeles 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 (n)(1) of this AD. Information may 

be emailed to: 9-ANM-LAACO-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, Los Angeles 

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) AMOCs approved previously for AD 

98–22–10, Amendment 39–10858 (63 FR 

57240, October 27, 1998), are approved as 

AMOCs for the corresponding provisions of 

this AD. 

(5) Accomplishment of the preventive 

modification in accordance with Boeing Alert 

Service Bulletin 737–53A1108, Revision 7, 

dated July 7, 2014, as required by paragraph 

(h) of this AD, is an AMOC for the structural 

modification specified in Boeing Alert 

Service Bulletin 737–53A1108 that is 

required by paragraph A. of AD 90–06–02, 

Amendment 39–6489, (55 FR 8372, March 7, 

1990), for the airplanes identified in 

paragraph (h) of this AD. 

(n) Related Information 

(1) For more information about this AD, 

contact Nenita Odesa, Aerospace Engineer, 

Airframe Branch, ANM–120L, FAA, Los 

Angeles ACO, 3960 Paramount Boulevard, 

Lakewood, CA 90712–4137; phone: 562–627– 

5234; fax: 562–627–5210; email: 

nenita.odesa@faa.gov. 

(2) Service information identified in this 

AD that is not incorporated by reference is 

available at the addresses specified in 

paragraph (o)(3) of this AD. 

(o) 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 737– 

53A1108, Revision 7, dated July 7, 2014. (ii) 

Reserved. 

(3) For Boeing 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; phone: 

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

5680; Internet https://

www.myboeingfleet.com. 

(4) You may view this service information 

at 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/ibrlocations.html. 

Issued in Renton, Washington, on July 10, 

2015. 

Jeffrey E. Duven, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2015–17977 Filed 7–23–15; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2015–0679; Directorate 

Identifier 2013–NM–182–AD; Amendment 

39–18211; AD 2015–15–02] 

RIN 2120–AA64 

Airworthiness Directives; Airbus 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: We are superseding 

Airworthiness Directive (AD) 2012–13– 

06, for all Airbus Model A300 series 

airplanes and all Model A300 B4–600, 

B4–600R, and F4–600R series airplanes, 

and Model A300 C4–605R Variant F 

airplanes (collectively called Model 

A300–600 series airplanes). AD 2012– 

13–06 required a one-time detailed 

inspection to determine the length of 

the fire shut-off valve (FSOV) bonding 

leads and for contact or chafing of the 

wires, and corrective actions if 

necessary. This new AD requires a new 

one-time detailed inspection of the 

FSOV bonding leads to ensure that the 

correct bonding leads are inspected, and 

corrective action if necessary. This AD 

was prompted by a determination that 

the description of the inspection area 

specified in the service information was 

misleading; therefore, some operators 

might have inspected incorrect bonding 

leads. We are issuing this AD to detect 

and correct contact or chafing of wires 

and the bonding leads, which, if not 

detected, could be a source of sparks in 

the wing trailing edge, and could lead 

to an uncontrolled engine fire. 

DATES: This AD becomes effective 

August 28, 2015. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in this AD 

as of August 28, 2015. 

ADDRESSES: You may examine the AD 

docket on the Internet at http://

www.regulations.gov/

#!docketDetail;D=FAA-2015-0679; 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 SAS, 

Airworthiness Office—EAW, 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. 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. It is also 

available on the Internet at http://

www.regulations.gov by searching for 

and locating Docket No. FAA–2015– 

0679. 

FOR FURTHER INFORMATION CONTACT: Dan 

Rodina, Aerospace Engineer, 

International Branch, ANM–116, 

Transport Airplane Directorate, FAA, 

1601 Lind Avenue SW., Renton, WA 


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98057–3356; telephone 425–227–2125; 

fax 425–227–1149. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to supersede AD 2012–13–06, 

Amendment 39–17108 (77 FR 40485, 

July 10, 2012). AD 2012–13–06 applied 

to all Airbus Model A300 series 

airplanes and all Model A300 B4–600, 

B4–600R, and F4–600R series airplanes, 

and Model A300 C4–605R Variant F 

airplanes (collectively called Model 

A300–600 series airplanes). The NPRM 

published in the Federal Register on 

March 31, 2015 (80 FR 17003). The 

NPRM was prompted by a 

determination that the description of the 

inspection area specified in the service 

information was misleading; therefore, 

some operators might have inspected 

incorrect bonding leads. The NPRM 

proposed to require a new one-time 

detailed inspection of the FSOV 

bonding leads to ensure that the correct 

bonding leads are inspected, and 

corrective action if necessary. We are 

issuing this AD to detect and correct 

contact or chafing of wires and the 

bonding leads, which, if not detected, 

could be a source of sparks in the wing 

trailing edge, and could lead to an 

uncontrolled engine fire. 

The European Aviation Safety Agency 

(EASA), which is the Technical Agent 

for the Member States of the European 

Union, has issued EASA Airworthiness 

Directive 2013–0204, dated September 

6, 2013 (referred to after this as the 

Mandatory Continuing Airworthiness 

Information, or ‘‘the MCAI’’), to correct 

an unsafe condition. The MCAI states: 

During a scheduled maintenance check, 

one operator reported inoperative Fire Shut 

Off Valve (FSOV). Investigations showed 

damage at wire located between engine 2 

hydraulic FSOV and wing rear spar, in the 

zones 575/675, and at bonding lead, located 

between wing rib 7A and rib 8 below 

hydraulic pressure lines. 

Similar inspections on different aeroplanes 

have shown that one of the causes of damage 

is the contact between bonding lead and the 

harness, due to over length of the bonding 

lead. 

This condition, if not detected and 

corrected, could lead to either: 

—A potential explosive condition on-ground 

if the FSOV, that is installed in fuel vapor 

zone is commanded to close position, or 

—a temporary uncontrolled engine fire, if 

combined with a fire event in the nacelle 

fed by an hydraulic leakage and not 

controlled by the fire extinguishing system. 

As the affected wire is not powered during 

normal operation, no defect can be detected 

unless a test is performed on the FSOV 

during maintenance check. 

EASA issued AD 2011–0084 [http://

ad.easa.europa.eu/blob/easa_ad_2011_

0084.pdf/AD_2011-0084_Superseded] which 

required a one-time [detailed] inspection of 

the wires [for contact or chafing] located 

between [LH/RH] engines hydraulic FSOV 

and wing rear spar in the zones 575/675, and 

the bonding lead [for length] that is located 

between rib 7A and rib 8 below hydraulic 

pressure lines, and corrective actions [repair 

of wires or replacement of bonding leads] 

depending on findings. 

It appeared that the original issue of the 

Airbus inspection Service Bulletins (SB’s) as 

well as EASA AD 2011–0084 might have 

caused possible misunderstandings on the 

exact bonding leads and wires that are 

required to be inspected. 

For the reasons described above, this 

[EASA] AD retains the requirements of EASA 

AD 2011–0084, which is superseded, and 

requires additional work on aeroplanes that 

have already been inspected in accordance 

with the instructions of the original issue of 

the SB’s. 

You may examine the MCAI in the AD 

docket on the Internet at http://

www.regulations.gov/

#!documentDetail;D=FAA-2015-0679- 

0002. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. We 

received no comments on the NPRM (80 

FR 17003, March 31, 2015) 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 except for minor editorial 

changes. We have determined that these 

minor changes: 

• Are consistent with the intent that 

was proposed in the NPRM (80 FR 

17003, March 31, 2015) for correcting 

the unsafe condition; and 

• Do not add any additional burden 

upon the public than was already 

proposed in the NPRM (80 FR 17003, 

March 31, 2015). 

Related Service Information Under 1 

CFR Part 51 

Airbus has issued Service Bulletin 

A300–24–0106, Revision 01, dated 

March 26, 2013 (for Model A300 series 

airplanes); and Service Bulletin A300– 

24–6108, Revision 01, dated March 26, 

2013 (for Model A300–600 series 

airplanes). The service information 

describes procedures for inspecting the 

FSOV bonding leads, corrective actions, 

and repair of the associated wires. This 

service information is reasonably 

available because the interested parties 

have access to it through their normal 

course of business or by the means 

identified in the ADDRESSES section of 

this AD. 

Costs of Compliance 

We estimate that this AD affects 123 

airplanes of U.S. registry. 

We estimate that it takes about 8 

work-hours per product to comply with 

the basic requirements of this AD. The 

average labor rate is $85 per work-hour. 

Required parts cost about $500 per 

product. Based on these figures, we 

estimate the cost of this AD on U.S. 

operators to be $145,140, or $1,180 per 

product. 

In addition, we estimate that any 

necessary follow-on actions take about 1 

work-hour and require parts costing 

$50, for a cost of $135 per product. We 

have no way of determining the number 

of products that may need these actions. 

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 


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Federal Register / Vol. 80, No. 142 / Friday, July 24, 2015 / Rules and Regulations 43927 

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-2015-0679; 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 

removing Airworthiness Directive (AD) 

2012–13–06, Amendment 39–17108 (77 

FR 40485, July 10, 2012), and adding the 

following new AD: 

2015–15–02 Airbus: Amendment 39–18211. 

Docket No. FAA–2015–0679; Directorate 

Identifier 2013–NM–182–AD. 

(a) Effective Date 

This AD becomes effective August 28, 

2015. 

(b) Affected ADs 

This AD replaces AD 2012–13–06, 

Amendment 39–17108 (77 FR 40485, July 10, 

2012). 

(c) Applicability 

This AD applies to the airplanes specified 

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

AD, certificated in any category, all 

manufacturer serial numbers. 

(1) Airbus Model A300 B2–1A, B2–1C, 

B2K–3C, B2–203, B4–2C, B4–103, and B4– 

203 airplanes. 

(2) Airbus Model A300 B4–601, B4–603, 

B4–620, B4–622, B4–605R, B4–622R, F4– 

605R, and F4–622R airplanes. 

(3) Airbus Model A300 C4–605R Variant F 

airplanes. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 24, Electrical Power. 

(e) Reason 

This AD was prompted by a determination 

that the description of the inspection area 

specified in the service information was 

misleading; therefore, some operators might 

have inspected incorrect bonding leads. We 

are issuing this AD to detect and correct 

contact or chafing of wires and the bonding 

leads, which, if not detected, could be a 

source of sparks in the wing trailing edge, 

and could lead to an uncontrolled engine 

fire. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Inspection of the Fire Shut-Off Valve 

(FSOV) Bonding Leads 

At the applicable time specified in 

paragraph (g)(1) or (g)(2) of this AD: Do a onetime detailed inspection to determine the 

length of the FSOV bonding leads, and to 

detect contact or chafing of the wires located 

on the left-hand (LH) and right-hand (RH) 

sides of the wing rear spar, in accordance 

with the Accomplishment Instructions of 

Airbus Service Bulletin A300–24–0106, 

Revision 01, dated March 26, 2013 (for Model 

A300 series airplanes); or Airbus Service 

Bulletin A300–24–6108, Revision 01, dated 

March 26, 2013 (for Model A300–600 series 

airplanes); as applicable. 

(1) For airplanes on which the inspection 

required by paragraph (g) of AD 2012–13–06, 

Amendment 39–17108 (77 FR 40485, July 10, 

2012), has not been done as of the effective 

date of this AD: Inspect within 4,500 flight 

hours or 30 months after August 14, 2012 

(the effective date of AD 2012–13–06), 

whichever occurs first. 

(2) For airplanes on which the inspection 

required by paragraph (g) of AD 2012–13–06, 

Amendment 39–17108 (77 FR 40485, July 10, 

2012), has been done as of the effective date 

of this AD: Inspect within 4,500 flight hours 

or 30 months after the effective date of this 

AD, whichever occurs first. 

(h) Corrective Action for FSOV Bonding 

Leads 

If, during the inspection required by 

paragraph (g) of this AD, the length of the 

bonding lead(s) is more than 80 millimeters 

(mm) (3.15 inches): Before further flight, 

replace the bonding lead(s) with a new 

bonding lead having a length equal to 80 mm 

± 2 mm (3.15 inches) ± 0.08 inch, in 

accordance with the Accomplishment 

Instructions of the applicable service 

information identified in paragraph (g) of this 

AD. 

(i) Repair of the Wires of the LH and RH 

Sides 

If, during the inspection required by 

paragraph (g) of this AD, any contact or 

chafing of the wires is found, repair the wires 

before further flight, in accordance with the 

Accomplishment Instructions of the 

applicable service information identified in 

paragraph (g) of this AD. 

(j) Parts Installation Prohibition 

As of August 14, 2012 (the effective date 

of AD 2012–13–06, Amendment 39–17108 

(77 FR 40485, July 10, 2012), no person may 

install any bonding lead longer than 80 mm 

± 2 mm (3.15 inches) ± 0.08 inch, located 

between the LH/RH engine hydraulic FSOV 

and wing rear spar in zones 575/675 on any 

airplane. 

(k) 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: 

Dan Rodina, Aerospace Engineer, 

International Branch, ANM–116, Transport 

Airplane Directorate, FAA, 1601 Lind 

Avenue SW., Renton, WA 98057–3356; 

telephone 425–227–2125; 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) Contacting the Manufacturer: As of the 

effective date of this AD, for any requirement 

in this AD to obtain corrective actions from 

a manufacturer, the action must be 

accomplished using a method approved by 

the Manager, International Branch, ANM– 

116, Transport Airplane Directorate, FAA; or 

the European Aviation Safety Agency 

(EASA); or Airbus’s EASA Design 

Organization Approval (DOA). If approved by 

the DOA, the approval must include the 

DOA-authorized signature. 

(l) Related Information 

Refer to Mandatory Continuing 

Airworthiness Information (MCAI) EASA 

Airworthiness Directive 2013–0204, dated 

September 6, 2013, for related information. 

This MCAI may be found in the AD docket 

on the Internet at http://www.regulations.gov 

by searching for and locating Docket No. 

FAA–2015–0679. 

(m) 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 August 28, 2015. 

(i) Airbus Service Bulletin A300–24–0106, 

Revision 01, dated March 26, 2013. 

(ii) Airbus Service Bulletin A300–24–6108, 

Revision 01, dated March 26, 2013. 

(4) For service information identified in 

this AD, contact Airbus SAS, Airworthiness 


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Office—EAW, 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. 

(5) 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. 

(6) 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 July 10, 

2015. 

Michael Kaszycki, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2015–17935 Filed 7–23–15; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2014–0748; Directorate 

Identifier 2014–NM–013–AD; Amendment 

39–18219; AD 2015–15–10] 

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 reports of wear of the 

trimmable horizontal stabilizer actuator 

(THSA). This AD requires repetitive 

inspections of the THSA for damage, 

and replacement if necessary; and 

replacement of the THSA after reaching 

a certain life limit. We are issuing this 

AD to detect and correct wear on the 

THSA, which would reduce the 

remaining life of the THSA, possibly 

resulting in premature failure and 

consequent reduced control of the 

airplane. 

DATES: This AD becomes effective 

August 28, 2015. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of August 28, 2015. 

ADDRESSES: You may examine the AD 

docket on the Internet at http://

www.regulations.gov/

#!docketDetail;D=FAA-2014-0748 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—EIAS, 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. It is also available on the Internet 

at http://www.regulations.gov by 

searching for and locating Docket No. 

FAA 2014–0748. 

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 October 16, 2014 (79 FR 

62072). 

The European Aviation Safety Agency 

(EASA), which is the Technical Agent 

for the Member States of the European 

Union, has issued EASA Airworthiness 

Directive 2014–0011R1, dated January 

17, 2014 (referred to after this as the 

Mandatory Continuing Airworthiness 

Information, or ‘‘the MCAI’’), to correct 

an unsafe condition. The MCAI states: 

In the frame of the A320 Extended Service 

Goal (ESG) project and the study on the 

Trimmable Horizontal Stabilizer Actuator 

(THSA), a sampling programme of in-service 

units has been performed and several cases 

of wear at different THSA levels were 

reported. 

This condition, if not detected and 

corrected, would reduce the remaining life of 

the THSA, possibly resulting in premature 

failure and consequent reduced control of the 

aeroplane. 

Prompted by these findings, Airbus issued 

Service Bulletin (SB) A320–27–1227 to 

provide THSA inspection instructions. 

For the reasons described above, this 

[EASA] AD requires repetitive inspections of 

the THSA and introduces a life limit for the 

THSA. 

This AD also requires a detailed 

inspection of the magnetic chip detector 

for metal particles, a spectrometric 

analysis of the oil drained from the 

THSA gearbox, a detailed inspection of 

the ballscrew and nut, and a detailed 

inspection of the upper and the lower 

attachments for damage. The corrective 

action is replacement of the THSA with 

a serviceable THSA. The compliance 

time for the THSA replacement ranges 

from before further flight to within 4 

months from drainage of the oil sample. 

You may examine the MCAI in the 

AD docket on the Internet at http://

www.regulations.gov/

#!documentDetail;D=FAA-2014-0748- 

0002. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. We 

have considered the comments received. 

The following presents the comments 

received on the NPRM (79 FR 62072, 

October 16, 2014) and the FAA’s 

response to each comment. 

Requests To Extend Compliance Time 

Airlines for America (A4A), on behalf 

of American Airlines (AAL), Delta 

Airlines (DAL), and United Airlines 

(UAL), requested that we extend the 

initial inspection compliance time in 

paragraph (g)(2) of the NPRM (79 FR 

62072, October 16, 2014) from 4 months 

to 12 months after the effective date of 

the AD. A4A stated that the fleet age of 

multiple U.S. carriers means that a large 

number of airplanes will require 

inspection in a short period of time, 

likely resulting in schedule disruptions 

and/or cancellations. 

We disagree with the commenters’ 

request. We base AD compliance times 

primarily on our assessment of safety 

risk. Some safety issues are more time 

sensitive than others. We consider the 

overall risk to the fleet, including the 

severity of the failure and the likelihood 

of the failure’s occurrence in 

development of the compliance time for 

the ADs. The FAA and EASA work 

closely with the respective 

manufacturers to ensure that all 

appropriate instructions and parts are 

available at the appropriate time to meet 

our collective safety goals, and that 

those goals are based on safety of the 

fleet. We have not changed this AD in 

this regard. 

Requests To Clarify Wording in 

Paragraphs (h) and (j) of the NPRM (79 

FR 62072, October 16, 2014) 

A4A, on behalf of UAL and JetBlue, 

requested that we clarify the wording of 


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