Federal Register / Vol. 82, No. 186 / Wednesday, September 27, 2017 / Rules and Regulations 44903 

(j) New Provision: No Alternative Actions or 

Intervals 

After the action required by paragraph (i) 

of this AD has been done, no alternative 

actions (e.g., inspections) or intervals may be 

used unless the actions or intervals are 

approved as an AMOC in accordance with 

the procedures specified in paragraph (k)(1) 

of this AD. 

(k) Other FAA AD Provisions 

The following provisions also apply to this 

AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, International 

Branch, Transport Standards Branch, 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, Transport 

Standards Branch, FAA, 1601 Lind Avenue 

SW., Renton, WA 98057–3356; telephone: 

425–227–1405; fax: 425–227–1149. 

Information may be emailed to: 9-ANM-116- 

AMOC-REQUESTS@faa.gov. 

(i) 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. 

(ii) AMOCs approved previously for AD 

2014–26–10 are approved as AMOCs for the 

corresponding provisions of paragraph (g) of 

this AD. 

(iii) AMOCs approved previously for AD 

2014–26–10, which are included in the 

AMOC letters specified in paragraphs 

(k)(1)(iii)(A) and (k)(1)(iii)(B), are approved 

as AMOCs for the provisions of paragraph (i) 

of this AD. 

(A) AMOC letter ANM–116–17–002R1, 

dated November 14, 2016. 

(B) AMOC letter ANM–116–17–323, dated 

June 12, 2017. 

(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 Section, Transport 

Standards Branch, FAA; or the European 

Aviation Safety Agency (EASA); or EASA 

Design Organization Approval (DOA). If 

approved by the DOA, the approval must 

include the DOA-authorized signature. 

(l) Related Information 

(1) Refer to Mandatory Continuing 

Airworthiness Information (MCAI) EASA AD 

2016–0093, dated May 13, 2016, 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–2017–0248. 

(2) For more information about this AD, 

contact Sanjay Ralhan, Aerospace Engineer, 

International Section, Transport Standards 

Branch, FAA, 1601 Lind Avenue SW., 

Renton, WA 98057–3356; telephone: 425– 

227–1405; fax: 425–227–1149. Information 

may be emailed to: 9-ANM-116-AMOCREQUESTS@faa.gov. 

(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 November 1, 2017. 

(i) Airbus A318/A319/A320/A321 

Airworthiness Limitations Section (ALS) Part 

4, ‘‘System Equipment Maintenance 

Requirements (SEMR),’’ Revision 03 at Issue 

02, dated January 22, 2016. 

(ii) Reserved. 

(4) The following service information was 

approved for IBR on February 25, 2015 (80 

FR 2813, January 21, 2015). 

(i) Airbus A318/A319/A320/A321 

Airworthiness Limitations Section, ALS Part 

4, ‘‘Aging Systems Maintenance,’’ Revision 

01, dated June 15, 2012. The revision level 

of this document is identified on only the 

title page and in the Record of Revisions. The 

revision date is not identified on the title 

page of this document. 

(ii) Reserved. 

(5) 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.airworth-eas@

airbus.com; Internet: http://www.airbus.com. 

(6) You may view this service information 

at the FAA, Transport Standards Branch, 

1601 Lind Avenue SW., Renton, WA. For 

information on the availability of this 

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

(7) 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 14, 2017. 

Jeffrey E. Duven, 

Director, System Oversight Division, Aircraft 

Certification Service. 

[FR Doc. 2017–20113 Filed 9–26–17; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2017–0498; Product 

Identifier 2016–NM–175–AD; Amendment 

39–19053; AD 2017–19–23] 

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) 2015–15– 

10, which applied to all Airbus Model 

A318, A319, A320, and A321 series 

airplanes. AD 2015–15–10 required 

repetitive inspections of the trimmable 

horizontal stabilizer actuator (THSA) for 

damage, and replacement if necessary; 

and replacement of the THSA after 

reaching a certain life limit. This AD 

requires repetitive detailed inspections 

of certain THSAs, and related 

investigative and corrective actions if 

necessary. This AD was prompted by 

the establishment of an additional life 

limit for the THSA, based on flight 

cycles. In addition, the THSA 

manufacturer has issued service 

information which, when accomplished, 

increases the life limit of the THSA. We 

are issuing this AD to address the unsafe 

condition on these products. 

DATES: This AD is effective November 1, 

2017. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of November 1, 2017. 

ADDRESSES: For service information 

identified in this final rule, 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.airworth-eas@airbus.com; 

Internet http://www.airbus.com. 

You may view this referenced service 

information at the FAA, Transport 

Standards Branch, 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–2017– 

0498. 

Examining the AD Docket 

You may examine the AD docket on 

the Internet at http:// 


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www.regulations.gov by searching for 

and locating Docket No. FAA–2017– 

0498; 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 address for the 

Docket Office (telephone 800–647–5527) 

is 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 20590. 

FOR FURTHER INFORMATION CONTACT: 

Sanjay Ralhan, Aerospace Engineer, 

International Section, Transport 

Standards Branch, 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 to supersede AD 2015–15–10, 

Amendment 39–18219 (80 FR 43928, 

July 24, 2015) (‘‘AD 2015–15–10’’). AD 

2015–15–10 applied to all Airbus Model 

A318, A319, A320, and A321 series 

airplanes. The NPRM published in the 

Federal Register on June 2, 2017 (82 FR 

25542). The NPRM was prompted by the 

establishment of an additional life limit 

for the THSA, based on flight cycles. 

The NPRM proposed to require 

repetitive detailed inspections of certain 

THSAs, and related investigative and 

corrective actions if necessary. We are 

issuing this AD to detect and correct 

wear of the THSA, which could reduce 

the remaining life of the THSA, possibly 

resulting in premature failure and 

consequent reduced controllability of 

the airplane. 

The European Aviation Safety Agency 

(EASA), which is the Technical Agent 

for the Member States of the European 

Union, has issued EASA Airworthiness 

Directive 2016–0184, dated September 

13, 2016 (referred to after this as the 

Mandatory Continuing Airworthiness 

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

an unsafe condition for all Airbus 

Model A318 and A319 series airplanes; 

Model A320–211, –212, –214, –231, 

–232, and –233 airplanes; and Model 

A321–111, –112, –131, –211, –212, 

–213, –231, and –232 airplanes. 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 was 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. 

Consequently, EASA issued AD 2014–0011 

(later revised) [which corresponds to AD 

2015–15–10] to require repetitive inspections 

of the THSA [and related investigative and 

corrective actions] and to introduce a life 

limit for the THSA, based on flight hours 

(FH). 

Since EASA AD 2014–0011R1 was issued, 

an additional life limitation has been 

established, based on flight cycles (FC). 

Furthermore, United Technologies 

Corporation Aerospace Systems (UTAS), the 

THSA manufacturer, issued an SB which, 

after accomplishment on THSA, increases the 

life limit of the THSA. 

For the reasons described above, this 

[EASA] AD retains the requirements of EASA 

AD 2014–0011R1, which is superseded, and 

introduces an additional FC life limit for the 

affected THSA. This [EASA] AD also 

provides a revised life limit for the THSA 

after UTAS SB accomplishment on that 

THSA. 

You may examine the MCAI in the 

AD docket on the Internet at http://

www.regulations.gov by searching for 

and locating Docket No. FAA–2017– 

0498. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. We 

considered the comments received. Air 

Line Pilots Association, International 

(ALPA) and United Airlines expressed 

their support for the NPRM. 

Changes Made to This AD 

The NPRM specified that a THSA that 

had been repaired in-shop as specified 

in UTAS Component Maintenance 

Manual 27–44–51 would be an 

equivalent method of compliance for the 

initial inspection required by paragraph 

(h) of this AD. We have revised 

paragraph (m) of this AD to specify that 

a THSA that has been repaired in-shop 

using a method approved by the 

Manager, International Section, 

Transport Standards Branch, FAA; or 

the EASA; or Airbus’s EASA Design 

Organization Approval (DOA), is 

acceptable for compliance with the 

initial inspection required by paragraph 

(h) of this AD. We have also added Note 

1 to paragraph (m) of this AD to 

reference UTAS Component 

Maintenance Manual 27–44–51 as an 

additional source of guidance for the inshop repair of the THSA. 

Conclusion 

We reviewed the relevant data, 

considered 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 minor changes: 

• Are consistent with the intent that 

was proposed in the NPRM for 

correcting the unsafe condition; and 

• Do not add any additional burden 

upon the public than was already 

proposed in the NPRM. 

We also determined that these 

changes will not increase the economic 

burden on any operator or increase the 

scope of this AD. 

Related Service Information Under 1 

CFR Part 51 

Airbus has issued Service Bulletin 

A320–27–1227, Revision 03, dated April 

29, 2016. This service information 

describes procedures for repetitive 

special detailed inspections for wear of 

the THSA, and related investigative and 

corrective actions. 

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. 

Costs of Compliance 

We estimate that this AD affects 1,182 

airplanes of U.S. registry. 

We estimate the following costs to 

comply with this AD: 

ESTIMATED COSTS

Action Labor cost Parts cost Cost per product Cost on U.S. operators 

Inspections ............. 6 work-hours × $85 per hour = 

$510 per inspection cycle.

$0 $510 per inspection cycle ........... $602,820 per inspection cycle. 


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We have received no definitive data 

that would enable us to provide cost 

estimates for the spectrometric analysis 

of the oil drained from the THSA 

gearbox. We estimate the following costs 

to do any necessary replacements or 

overhauls 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 or overhauls: 

ON-CONDITION COSTS

Action Labor cost Parts cost Cost per 

product 

Replacement of THSA (retained from AD 2015–15– 

10).

11 work-hours × $85 per hour = $935 ......................... $240,000 $240,935 

Overhaul of THSA (new action) ................................... 66 work-hours × $85 per hour = $5,610 ...................... 115,000 120,610 

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. 

This AD is issued in accordance with 

authority delegated by the Executive 

Director, Aircraft Certification Service, 

as authorized by FAA Order 8000.51C. 

In accordance with that order, issuance 

of ADs is normally a function of the 

Compliance and Airworthiness 

Division, but during this transition 

period, the Executive Director has 

delegated the authority to issue ADs 

applicable to transport category 

airplanes to the Director of the System 

Oversight Division. 

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. 

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) 

2015–15–10, Amendment 39–18219 (80 

FR 43928, July 24, 2015), and adding the 

following new AD: 

2017–19–23 Airbus: Amendment 39–19053; 

Docket No. FAA–2017–0498; Product 

Identifier 2016–NM–175–AD. 

(a) Effective Date 

This AD is effective November 1, 2017. 

(b) Affected ADs 

This AD replaces AD 2015–15–10, 

Amendment 39–18219 (80 FR 43928, July 24, 

2015) (‘‘AD 2015–15–10’’). 

(c) Applicability 

This AD applies to the airplanes identified 

in paragraphs (c)(1) through (c)(4) of this AD, 

certificated in any category, all manufacturer 

serial numbers. 

(1) Airbus Model A318–111, –112, –121, 

and –122 airplanes. 

(2) Airbus Model A319–111, –112, –113, 

–114, –115, –131, –132, and –133 airplanes. 

(3) Airbus Model A320–211, –212, –214, 

–231, –232, and –233 airplanes. 

(4) Airbus Model A321–111, –112, –131, 

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

(d) Subject 

Air Transport Association (ATA) of 

America Code 27, Flight controls. 

(e) Reason 

This AD was prompted by reports of wear 

at different levels in the trimmable horizontal 

stabilizer actuator (THSA). We are issuing 

this AD to detect and correct wear of the 

THSA, which could reduce the remaining life 

of the THSA, possibly resulting in premature 

failure and consequent reduced 

controllability of the airplane. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Serviceable THSA Definition 

For the purposes of this AD, a serviceable 

THSA is a THSA that does not exceed the life 

limits as identified in table 1 to paragraphs 

(g) and (j) of this AD. 

TABLE 1 TO PARAGRAPHS (G) AND (J) OF THIS AD—THSA Life Limits 

Configuration, based on service bulletin (SB) embodiment Compliance time (whichever occurs first) 

THSA on which United Technologies Corporation Aerospace Systems 

(UTAS) SB 47145–27–19 has not been embodied.

Before exceeding 67,500 flight hours (FH) since first installation on an 

airplane, or before exceeding 48,000 flight cycles (FC) since first installation on an airplane. 


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TABLE 1 TO PARAGRAPHS (G) AND (J) OF THIS AD—THSA Life Limits—Continued 

Configuration, based on service bulletin (SB) embodiment Compliance time (whichever occurs first) 

THSA on which UTAS SB 47145–27–19 has been embodied ............... Before exceeding 52,500 FH after embodiment of UTAS SB 47145–

27–19 on an airplane, without exceeding 120,000 FH since first installation on an airplane; or before exceeding 27,000 FC after embodiment of UTAS SB 47145–27–19 on an airplane, without exceeding 75,000 FC since first installation on an airplane. 

(h) Repetitive Inspection and Related 

Investigative Actions 

For any airplane on which UTAS Service 

Bulletin 47145–27–19 has not been 

embodied: Before the THSA exceeds 48,000 

flight hours or 30,000 flight cycles, 

whichever occurs first since first installation 

on an airplane, do a special detailed 

inspection of the THSA and do all applicable 

related investigative actions, in accordance 

with the Accomplishment Instructions of 

Airbus Service Bulletin A320–27–1227, 

Revision 03, dated April 29, 2016. Do all 

applicable related investigative actions at the 

applicable times specified in paragraph 1.E., 

‘‘Compliance’’ of Airbus Service Bulletin 

A320–27–1227, Revision 03, dated April 29, 

2016. Repeat the inspections thereafter at 

intervals not to exceed 24 months. 

(i) Corrective Action 

If, during any inspection required by 

paragraph (h) of this AD, any finding as 

described in the Accomplishment 

Instructions of Airbus Service Bulletin A320– 

27–1227, Revision 03, dated April 29, 2016, 

is identified: At the applicable time 

(depending on the applicable finding) 

specified in paragraph 1.E., ‘‘Compliance,’’ of 

Airbus Service Bulletin A320–27–1227, 

Revision 03, dated April 29, 2016, replace the 

THSA with a serviceable THSA, as specified 

in paragraph (g) of this AD, in accordance 

with the Accomplishment Instructions of 

Airbus Service Bulletin A320–27–1227, 

Revision 03, dated April 29, 2016. 

(j) THSA Replacement 

Within the applicable compliance time 

specified in table 1 to paragraphs (g) and (j) 

of this AD, replace each THSA with a 

serviceable THSA, as specified in paragraph 

(g) of this AD, in accordance with the 

Accomplishment Instructions of Airbus 

Service Bulletin A320–27–1227, Revision 03, 

dated April 29, 2016. 

(k) Replacement of a THSA: Not Terminating 

Action 

Replacement of a THSA on an airplane, as 

required by paragraph (i) or (j) of this AD, 

does not constitute terminating action for the 

repetitive inspections required by paragraph 

(h) of this AD for that airplane, unless the 

THSA has been overhauled as specified in 

UTAS Service Bulletin 47145–27–19 (i.e., 

post-service bulletin). 

(l) Optional Terminating Action: Overhaul of 

THSA 

Accomplishment of a modification of an 

airplane by installing a THSA that has been 

overhauled as specified in UTAS Service 

Bulletin 47145–27–19 constitutes terminating 

action for the repetitive inspections required 

by paragraph (h) of this AD, provided that, 

following modification, no THSA is 

reinstalled on the airplane unless it has been 

overhauled as specified in UTAS Service 

Bulletin 47145–27–19. 

(m) Replacement THSA Equivalency 

As of the effective date of this AD: A THSA 

that has been repaired in-shop is acceptable 

for compliance with the initial inspection 

required by paragraph (h) of this AD, 

provided that repair was done using a 

method approved by the Manager, 

International Section, Transport Standards 

Branch, FAA; or the European Aviation 

Safety Agency (EASA); or Airbus’s EASA 

Design Organization Approval (DOA). 

Note 1 to paragraph (m) of this AD: 

Guidance for THSA repair in-shop can be 

found in UTAS Component Maintenance 

Manual 27–44–51. 

(n) Parts Installation Limitation 

As of the effective date of this AD: Do not 

install on any airplane a THSA unless it is 

a serviceable THSA as specified in paragraph 

(g) of this AD. 

(o) Credit for Previous Actions 

This paragraph provides credit for the 

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

this AD, if those actions were performed 

before the effective date of this AD using any 

of the service information specified in 

paragraphs (o)(1), (o)(2), or (o)(3) of this AD. 

(1) Airbus Service Bulletin A320–27–1227, 

dated July 1, 2013, which is not incorporated 

by reference in this AD. 

(2) Airbus Service Bulletin A320–27–1227, 

Revision 01, dated October 7, 2013, which 

was incorporated by reference in AD 2015– 

15–10. 

(3) Airbus Service Bulletin A320–27–1227, 

Revision 02, dated February 2, 2015, which 

is not incorporated by reference in this AD. 

(p) Other FAA AD Provisions 

The following provisions also apply to this 

AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, International 

Section, Transport Standards Branch, 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 Section, send it 

to the attention of the person identified in 

paragraph (q)(2) of this AD. Information may 

be emailed to: 9-ANM-116-AMOCREQUESTS@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. 

(2) Contacting the Manufacturer: 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 Section, 

Transport Standards Branch, FAA; or the 

EASA; or Airbus’s EASA DOA. If approved 

by the DOA, the approval must include the 

DOA-authorized signature. 

(3) Required for Compliance (RC): If any 

service information contains procedures or 

tests that are identified as RC, those 

procedures and tests must be done to comply 

with this AD; any procedures or tests that are 

not identified as RC are recommended. Those 

procedures and tests that are not identified 

as RC may be deviated from using accepted 

methods in accordance with the operator’s 

maintenance or inspection program without 

obtaining approval of an AMOC, provided 

the procedures and tests identified as RC can 

be done and the airplane can be put back in 

an airworthy condition. Any substitutions or 

changes to procedures or tests identified as 

RC require approval of an AMOC. 

(q) Related Information 

(1) Refer to Mandatory Continuing 

Airworthiness Information (MCAI) EASA 

Airworthiness Directive 2016–0184, dated 

September 13, 3016, 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–2017–0498. 

(2) For more information about this AD, 

contact Sanjay Ralhan, Aerospace Engineer, 

International Section, Transport Standards 

Branch, FAA, 1601 Lind Avenue SW., 

Renton, WA 98057–3356; telephone 425– 

227–1405; fax 425–227–1149. 

(3) Service information identified in this 

AD that is not incorporated by reference is 

available at the addresses specified in 

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

(r) 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 A320–27–1227, 

Revision 03, dated April 29, 2016. 

(ii) Reserved. 

(3) For Airbus service information 

identified in this AD, contact Airbus, 

Airworthiness Office—EIAS, 1 Rond Point 

Maurice Bellonte, 31707 Blagnac Cedex, 


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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 Standards Branch, 

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 

September 14, 2017. 

Jeffrey E. Duven, 

Director, System Oversight Division, Aircraft 

Certification Service. 

[FR Doc. 2017–20567 Filed 9–26–17; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2017–0813; Product 

Identifier 2017–NM–109–AD; Amendment 

39–19059; AD 2017–20–02] 

RIN 2120–AA64 

Airworthiness Directives; Airbus 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule; request for 

comments. 

SUMMARY: We are superseding 

Airworthiness Directive (AD) 2017–13– 

05, which applied to all Airbus Model 

A330–200, A330–300, A340–200, A340– 

300, A340–500, and A340–600 series 

airplanes. AD 2017–13–05 required an 

inspection, corrective actions if 

necessary, lubrication of the ball-nut, 

modification of the trimmable 

horizontal stabilizer actuator (THSA), 

and additional work for previously 

modified airplanes. For certain 

airplanes, AD 2017–13–05 required 

installation of an electronic harness, 

terminating actions, and a ball-screw 

assembly inspection. This AD clarifies 

the formatting of a figure in the 

published version of AD 2017–13–05. 

This AD was prompted by reports 

indicating that affected parties 

misinterpreted the intent of a figure as 

formatted in the published version of 

AD 2017–13–05, which could result in 

a negative effect on compliance. We are 

issuing this AD to address the unsafe 

condition on these products. 

DATES: This AD is effective October 12, 

2017. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in this AD 

as of August 28, 2017 (82 FR 34251, July 

24, 2017). 

We must receive comments on this 

AD by November 13, 2017. 

ADDRESSES: You may send comments, 

using the procedures found in 14 CFR 

11.43 and 11.45, by any of the following 

methods: 

• Federal eRulemaking Portal: Go to 

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

instructions for submitting comments. 

• Fax: 202–493–2251. 

• Mail: U.S. Department of 

Transportation, Docket Operations, M– 

30, West Building Ground Floor, Room 

W12–140, 1200 New Jersey Avenue SE., 

Washington, DC 20590. 

• Hand Delivery: U.S. Department of 

Transportation, Docket Operations, M– 

30, West Building Ground Floor, Room 

W12–140, 1200 New Jersey Avenue SE., 

Washington, DC, between 9 a.m. and 5 

p.m., Monday through Friday, except 

Federal holidays. 

For Airbus service information 

identified in this final rule, 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.airworth-eas@

airbus.com; Internet: http://

www.airbus.com. 

You may view this referenced service 

information at the FAA, Transport 

Standards Branch, 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–2017– 

0813. 

Examining the AD Docket 

You may examine the AD docket on 

the Internet at http://

www.regulations.gov by searching for 

and locating Docket No. FAA–2017– 

0813; 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 Office (telephone 800–647– 

5527) is 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 20590. 

FOR FURTHER INFORMATION CONTACT: 

Vladimir Ulyanov, Aerospace Engineer, 

International Section, Transport 

Standards Branch, FAA, 1601 Lind 

Avenue SW., Renton, WA 98057–3356; 

telephone 425–227–1138; fax 425–227– 

1149. 

SUPPLEMENTARY INFORMATION: 

Discussion 

On June 15, 2017, we issued AD 

2017–13–05, Amendment 39–18935 (82 

FR 34251, July 24, 2017) (‘‘AD 2017–13– 

05’’), which applied to all Airbus Model 

A330–200, A330–300, A340–200, A340– 

300, A340–500, and A340–600 series 

airplanes. AD 2017–13–05 was 

prompted by the need for a modification 

that automatically detects failure of the 

ball-screw assembly. AD 2017–13–05 

required an inspection, corrective 

actions if necessary, lubrication of the 

ball-nut, modification of the trimmable 

horizontal stabilizer actuator (THSA), 

and additional work for previously 

modified airplanes. For certain 

airplanes, AD 2017–13–05 required 

installation of an electronic harness, 

terminating actions, and a ball-screw 

assembly inspection. We issued AD 

2017–13–05 to detect and correct wear 

on the THSA, possibly resulting in 

damage to the ball-screw and fail-safe 

nut, which could jam the THSA and 

result in reduced control of the airplane. 

Since we issued AD 2017–13–05, we 

have received reports indicating that 

affected parties could misinterpret the 

identity of applicable service 

information to use for the modification, 

due to the formatting of figure 2 to 

paragraphs (h) and (i) in the published 

version of AD 2017–13–05. Since the 

published figure could result in a 

negative effect on compliance, we have 

determined that clarification of the 

formatting of the published figure is 

necessary. 

The European Aviation Safety Agency 

(EASA), which is the Technical Agent 

for the Member States of the European 

Union, has issued EASA AD 2014–0219, 

dated September 29, 2014 (referred to 

after this as the Mandatory Continuing 

Airworthiness Information, or ‘‘the 

MCAI’’), to correct an unsafe condition 

for all Airbus Model A330 and Model 

A340 series airplanes. (Model A330– 

223F and A330–243F airplanes were 

removed from AD 2017–13–05 to 

correspond with the MCAI.) The EASA 

AD is referenced in AD 2017–13–05. 

EASA has not revised its AD since the 

issuance of AD 2017–13–05. 

You may examine the MCAI in the 

AD docket on the Internet at http://

www.regulations.gov by searching for 

and locating Docket No. FAA–2017– 

0813. 


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