Airworthiness Directive · Amendment 39-19053 · Flight controls
Airbus Airplanes
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.
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.
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.
| 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. |
| 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. |
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 (i.e., post-service bulletin).
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.
The aircraft, engines and makers this AD names, by the model designations in its text. A model listed here may still be outside the AD's serial ranges.
