Airworthiness Directive · Amendment 39-21667 · Main rotor gearbox
Airbus Helicopters
This AD applies to all Airbus Helicopters Model AS332L2 and EC225LP helicopters, certificated in any category.
The FAA is superseding Airworthiness Directive (AD) 2016-12- 51, which applied to all Airbus Helicopters Model AS332L2 and Model EC225LP helicopters. AD 2016-12-51 prohibited all further flight of Model AS332L2 and Model EC225LP helicopters. This AD requires replacing certain second stage planet gear assemblies, removing certain epicyclic modules, installing a full flow magnetic plug (FFMP), revising the existing rotorcraft flight manual (RFM) for your helicopter, repetitively inspecting the main gearbox (MGB) particle detectors, repetitively inspecting the MGB oil filter and oil cooler, and corrective action if necessary, as specified in a European Union Aviation Safety Agency (EASA) AD, which is incorporated by reference. The actions specified in this AD terminate the flight prohibition. The FAA is issuing this AD to address the unsafe condition on these products.
Except as specified in paragraph (h) of this AD: Comply with all required actions and compliance times specified in, and in accordance with, European Union Aviation Safety Agency (EASA) AD 2017-0134R2, dated April 16, 2020 (EASA AD 2017-0134R2).
(1) Where EASA AD 2017-0134R2 refers to the effective dates specified in paragraphs (h)(1)(i) through (v) of this AD, this AD requires using the effective date of this AD.
(i) The effective date of EASA AD 2017-0134R2.
(ii) October 13, 2016 (the effective date of EASA AD 2016-0199, dated October 7, 2016).
(iii) March 20, 2017 (the effective date of EASA AD 2017-0050-E, dated March 17, 2017).
(iv) June 30, 2017 (the effective date of EASA AD 2017-0111, dated June 23, 2017).
(v) August 1, 2017 (the effective date of EASA AD 2017-0134, dated July 27, 2017).
(2) The “Remarks” section of EASA AD 2017-0134R2 does not apply to this AD.
(3) Where any service information referred to in EASA AD 2017-0134R2 specifies to discard certain parts after they have been removed from the helicopter, this AD requires removing those parts from service.
(4) Where paragraph (2) of EASA AD 2017-0134R2 specifies to replace a part before exceeding the applicable “new service life limit,” this AD requires removing that part from service.
(5) Where any service information referred to in EASA AD 2017-0134R2 specifies to return certain parts to the manufacturer, including for overhaul, after they have been removed from the helicopter, this AD does not include that requirement.
(6) Where EASA AD 2017-0134R2 refers to flight hours (FH), this AD requires using hours time-in-service.
(7) Where any service information referred to in EASA AD 2017-0134R2 specifies to perform a metallurgical analysis and contact the manufacturer if unsure about the characterization of the particles collected, this AD does require characterization of the particles collected, however this AD does not require contacting the manufacturer to determine the characterization of the particles collected.
(8) Where EASA AD 2017-0134R2 requires actions during each “after last flight” of the day (ALF) inspection, this AD requires those actions before the first flight of each day.
(9) Where any service information referred to in EASA AD 2017-0134R2 specifies to do the actions identified in paragraphs (h)(9)(i) through (iv) of this AD, this AD does not include those requirements.
(i) Watch a video for removing the grease from the full flow magnetic plug (FFMP), using a cleaning agent, and collecting particles.
(ii) Return affected planetary gear assembly to the manufacturer for module overhaul.
(iii) Contact the approved repair station/Airbus Helicopters if the reason for a repair to an epicyclic module is unknown and inform/contact Airbus Helicopters.
(iv) Contact the approved repair station/Airbus Helicopters depending on who performed the last overhaul (RG) to determine if a repair has been done on the second stage planet gears since new.
(10) Where any service information referred to in EASA AD 2017-0134R2 specifies that retrofit of the planet gear of the main gearbox (MGB) can only be done by Airbus Helicopters or Airbus Helicopters approved repair centers, this AD does not require that the retrofit of the planet gear be done only by Airbus Helicopters or Airbus Helicopters approved repair centers. For this AD the retrofit can also be done by an FAA-approved repair station.
(11) Where paragraph (5) of EASA AD 2017-0134R2 specifies accomplishing the FFMP additional work within 3 months after August 1, 2017, this AD requires accomplishing the FFMP additional work within 4 months after the effective date of this AD.
(12) Where paragraph (6) of EASA AD 2017-0134R2 specifies to “inform all flight crews and, thereafter, operate the helicopter accordingly,” this AD does not require those actions.
(13) Where any service information referred to in EASA AD 2017-0134R2 specifies that if any 16NCD13 particles are found you are to take a 1-liter sample of oil and send it to the manufacturer, this AD does not require those actions.
(14) Where any service information referred to in EASA AD 2017-0134R2 specifies “Do not resume flights until corrective action(s) are agreed by Airbus Helicopters,” or to contact Airbus Helicopters before resuming flights “if further particles are collected during the close monitoring period” for this AD, you must repair before further flight using a method specified in paragraph (h)(14)(i) or (ii) of this AD.
(i) In accordance with FAA approved procedures.
(ii) The procedures specified in Appendix 4.A., Particle Analysis, of Airbus Helicopters Emergency Alert Service Bulletin 05A049, Revision 6, dated July 25, 2017; or Emergency Alert Service Bulletin 05.01.07, Revision 6, dated July 27, 2017, as applicable, except as required by paragraphs (h)(5), (7), and (13) of this AD.
(15) Where the service information identified in EASA AD 2017-0134R2 specifies to report inspection results to Airbus Helicopters, for this AD, report the inspection results at the applicable time specified in paragraph (h)(15)(i) or (ii) of this AD.
(i) If the inspection was done on or after the effective date of this AD: Submit the report within 30 days after the date of the inspection.
(ii) If the inspection was done before the effective date of this AD: Submit the report within 30 days after the effective date of this AD.
