Federal Aviation Administration (FAA), Department of Transportation (DOT).
Final rule.
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.
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.
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
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
You may examine the AD docket on the Internet at
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.
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
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
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.
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 in-shop repair of the THSA.
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.
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
We estimate that this AD affects 1,182 airplanes of U.S. registry.
We estimate the following costs to comply with this AD:
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:
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.
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.
Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety.
Accordingly, under the authority delegated to me by the Administrator, the FAA amends 14 CFR part 39 as follows:
49 U.S.C. 106(g), 40113, 44701.
This AD is effective November 1, 2017.
This AD replaces AD 2015–15–10, Amendment 39–18219 (80 FR 43928, July 24, 2015) (“AD 2015–15–10”).
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.
Air Transport Association (ATA) of America Code 27, Flight controls.
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.
Comply with this AD within the compliance times specified, unless already done.
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.
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.
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.
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.
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 (
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.
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.
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.
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.
The following provisions also apply to this AD:
(1)
(2)
(3)
(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
(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.
(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,
(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: