Airworthiness Directive · Amendment 39-18270 · 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) 2011-19-04, for all Airbus Model A318, A319, A320, and A321 series airplanes. AD 2011-19-04 required repetitive inspections for cracking of the left- hand and right-hand inboard and outboard elevator servo-control rod eye-ends, and corrective actions if necessary. This new AD requires an inspection to determine if certain elevator servo-control parts are installed, and replacement if necessary. This AD was prompted by a determination that certain elevator servo-control parts that do not conform to the approved type design have been installed and may have the potential of cracks in the rod eye-end. We are issuing this AD to detect and correct rod eye-end cracking, which could result in uncontrolled elevator surface and consequent reduced control of the airplane.
This paragraph restates the requirements of paragraph (g) of AD 2011-19-04, Amendment 39-16809 (76 FR 57630, September 16, 2011), with no changes.
(1) At the applicable times specified in paragraphs (g)(1)(i) and (g)(1)(ii) of this AD: Inspect both the left-hand and right-hand inboard elevator servo-control rod eye-ends for cracking, in accordance with the instructions of Airbus All Operators Telex (AOT) A320-27A1186, Revision 04, dated April 3, 2009; or the Accomplishment Instructions of Airbus Service Bulletin A320-27A1186, Revision 07, dated March 2, 2011. As of October 21, 2011 (the effective date of AD 2011-19-04, Amendment 39-16809 (76 FR 57630, September 16, 2011)), use Airbus Service Bulletin A320-27A1186, Revision 07, dated March 2, 2011.
(i) For airplanes that have accumulated 10,000 total flight cycles or more as of September 22, 2009 (the effective date of AD 2009-17-04, Amendment 39-15995 (74 FR 41611, August 18, 2009)): At the later of the times specified in paragraphs (g)(1)(i)(A) and (g)(1)(i)(B) of this AD.
(A) Within 1,500 flight cycles after September 22, 2009 (the effective date of AD 2009-17-04, Amendment 39-15995 (74 FR 41611, August 18, 2009)).
(B) Within 1,500 flight cycles after accumulating 10,000 total flight cycles since first flight of the airplane.
(ii) For airplanes that have accumulated less than 10,000 total flight cycles as of September 22, 2009 (the effective date of AD 2009-17-04, Amendment 39-15995 (74 FR 41611, August 18, 2009)): At the later of the times specified in paragraphs (g)(1)(ii)(A) and (g)(1)(ii)(B) of this AD.
(A) Before the accumulation of 5,000 total flight cycles.
(B) Within 20 months after October 21, 2011 (the effective date of AD 2011-19-04, Amendment 39-16809 (76 FR 57630, September 16, 2011)) but no later than before the accumulation of 11,500 total flight cycles.
(2) At the applicable time specified in paragraphs (g)(2)(i) and (g)(2)(ii) of this AD: Inspect both the left-hand and right-hand outboard elevator servo-control rod eye-ends for cracking, in accordance with the instructions of Airbus AOT A320-27A1186, Revision 04, dated April 3, 2009; or the Accomplishment Instructions of Airbus Service Bulletin A320-27A1186, Revision 07, dated March 2, 2011. As of October 21, 2011 (the effective date of AD 2011-19-04, Amendment 39-16809 (76 FR 57630, September 16, 2011)), use Airbus Service Bulletin A320-27A1186, Revision 07, dated March 2, 2011.
(i) For airplanes that have accumulated 10,000 total flight cycles or more as of September 22, 2009 (the effective date of AD 2009-17-04, Amendment 39-15995 (74 FR 41611, August 18, 2009)): At the later of the times specified in paragraphs (g)(2)(i)(A) and (g)(2)(i)(B) of this AD.
(A) Within 3,000 flight cycles after September 22, 2009 (the effective date of AD 2009-17-04, Amendment 39-15995 (74 FR 41611, August 18, 2009)).
(B) Within 3,000 flight cycles after accumulating 10,000 total flight cycles since first flight of the airplane.
(ii) For airplanes that have accumulated less than 10,000 total flight cycles as of September 22, 2009 (the effective date of AD 2009-17-04, Amendment 39-15995 (74 FR 41611, August 18, 2009)): At the later of the times specified in paragraphs (g)(2)(ii)(A) and (g)(2)(ii)(B) of this AD.
(A) Before the accumulation of 7,500 total flight cycles.
(B) Within 40 months after October 21, 2011 (the effective date of AD 2011-19-04, Amendment 39-16809 (76 FR 57630, September 16, 2011)), but no later than before the accumulation of 13,000 total flight cycles.
This paragraph restates the requirements of paragraph (h) of AD 2011-19-04, Amendment 39-16809 (76 FR 57630, September 16, 2011), with no changes. Repeat the inspections of the left-hand and right-hand inboard and outboard elevator servo-control rod eye-ends for cracking as required by paragraphs (g)(1) and (g)(2) of this AD at the later of the times specified in paragraph (h)(1) or (h)(2) of this AD. Repeat the inspections thereafter at intervals not to exceed 5,000 flight cycles.
(1) Within 5,000 flight cycles after the last inspection required by paragraph (g)(1) or (g)(2) of this AD as applicable.
(2) Within 6 months after October 21, 2011 (the effective date of AD 2011-19-04, Amendment 39-16809 (76 FR 57630, September 16, 2011)).
This paragraph restates the requirements of paragraph (i) of AD 2011-19-04, Amendment 39-16809 (76 FR 57630, September 16, 2011), with no changes. If any cracking is found during any inspection required by paragraph (g) or (h) of this AD, before further flight, accomplish all applicable corrective actions, in accordance with the Accomplishment Instructions and figures of Airbus Service Bulletin A320-27A1186, Revision 07, dated March 2, 2011.
This paragraph restates the requirements of paragraph (j) of AD 2011-19-04, Amendment 39-16809 (76 FR 57630, September 16, 2011), with a new exception. As of October 21, 2011 (the effective date of AD 2011-19-04, Amendment 39-16809 (76 FR 57360, September 16, 2011)), and except as required by paragraph (p) of this AD, no person may install on any airplane an elevator servo-control rod eye-end unless it is new or has been inspected in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320-27A1186, Revision 07, dated March 2, 2011, with no crack findings.
As of the effective date of this AD: At the later of the times specified in paragraphs (k)(1) and (k)(2) of this AD, do an inspection to determine whether any elevator control part having part number (P/N) 31075-0xx, 31075-1xx, or 31075-3xx is installed. A review of airplane maintenance records is acceptable in lieu of this inspection if the part numbers of the elevator control parts can be conclusively determined from that review.
(1) Concurrently with the accomplishment of the next inspection required by paragraph (g) or (h) of this AD.
(2) Within 30 days after the effective date of this AD.
If the inspection required by paragraph (k) of this AD reveals that any elevator servo-controls having P/Ns 31075-0xx, 31075-1xx, or 31075-3xx are installed: Before further flight, do the actions specified in paragraph (l)(1) or (l)(2) of this AD.
(1) Replace all elevator servo-controls having P/N 31075-0xx, 31075-1xx, or 31075-3xx with serviceable parts having P/N 31075-2xx or 31075-4xx, as applicable, 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). Serviceable parts are those that have been inspected for cracks in the rod eye-ends without any crack findings, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320-27A1186, Revision 07, dated March 2, 2011.
(2) Replace all elevator servo-controls having P/N 31075-0xx, 31075-1xx, or 31075-3xx with serviceable parts having P/N 31075-6xx or 31075-8xx, as applicable, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320-27-1223, dated September 3, 2013; or UTC Aerospace Systems Service Bulletin 31075-27-22, dated July 2, 2013.
Modification of an airplane by replacing all 4 elevator servo-control rod eye-ends with modified (i.e. re-greasable) parts, and re-identification of those elevator servo-controls to P/N 31075-6xx or P/N 31075-8xx, as applicable, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320-27-1223, dated September 3, 2013; constitutes terminating action for the requirements of paragraphs (g), (h), (k), and (l) of this AD.
Note 1 to paragraph (m) of this AD: Maintenance Review Board Report task reference 27.34.00/06, Lubrication of Elevator Servo-control Rod Eye End Bearing, is applicable to elevator servo-controls having P/N 31075-6xx or P/N 31075-8xx.
Airplanes on which Airbus Modification 154554 (installation of servo-controls having P/N 31075-6xx or P/N 31075-8xx, fitted with modified rod eye-end roller bearing) has been embodied in production are not affected by the requirements of paragraphs (g), (h), (k), and (l) of this AD, provided that no elevator servo-control having P/N 31075-0xx, or P/N 31075-1xx, or P/N 31075-2xx, or P/N 31075-3xx, or P/N 31075-4xx, fitted with rod eye-end assembly P/N 341203-xxx, has been reinstalled since first flight.
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.
