Airworthiness directives › 2018-04-13
AD 2018-04-13 Airworthiness Directives; Honeywell International Inc. Turbofan Engines
Applicability*9
This AD applies to all Honeywell International Inc. AS907-1-1A model turbofan engines with engine electronic control unit (ECU), part numbers (P/Ns) 2119576-1001 through -1011, installed; AS907-2-1A model turbofan engines with ECU, P/N 2119576-1102, installed; AS907-2-1G model turbofan engines with ECU, P/Ns 2119576-3002 and -3102, installed; and AS907-3-1E model turbofan engines with ECU, P/Ns 2119576-4102 and -4103, installed with applicable engine serial numbers (S/Ns) in Table 3 of Honeywell Service Bulletin (SB) AS907-76-9021, Revision 1, dated April 20, 2017 that are not sealed in the areas identified in Figures 1 through 13 of Honeywell SB AS907-76-9021, Revision 1, dated April 20, 2017.
Compliance
Comply with this AD within the compliance times specified, unless already done.
Required actions
(1) For applicable engines and ECUs, within 200 hours time in service, or 9 months after the effective date of this AD, whichever occurs first, do the following: (i) If no sealant has been applied to the ECU in the areas identified in Figures 1 through 13 of Honeywell SB AS907-76-9021, Revision 1, dated April 20, 2017, apply sealant to the ECU using the Accomplishment Instructions, paragraph 3.C., of Honeywell SB AS907-76-9021, Revision 1, dated April 20, 2017. (ii) Reserved. (2) Within 60 days after the effective date of this AD, for all airplanes that have an affected engine installed with an affected ECU not in compliance with paragraph (g)(1) of this AD, insert a copy of Figure 1, 2, or 3 to paragraph (g) of this AD, as applicable to your airplane, into the Emergency Procedures Section of the Airplane Flight Manual (AFM) and perform the following steps as necessary: (i) If a cyan warning is announced, before next flight, check the current fault messages in the Maintenance Data Computer (MDC)/Onboard Messaging System (OMS) for any of the following: (A) FADEC ECU A (B) FADEC ECU B (C) THROTTLE LEVER 1A (D) THROTTLE LEVER 1B (E) THROTTLE RIGGING 1A (F) THROTTLE RIGGING 1B (ii) Replace the ECU if any of the fault messages listed in paragraph (g)(2)(i) of this AD are in the MDC OMS. Refer to Honeywell Operating Information Letter OIAS907-0001R00, dated March 14, 2017, for guidance on returning and replacing the ECU. (iii) Continued flight is permitted if none of the fault messages listed in paragraph (g)(2)(i) of this AD are in the MDC OMS, or if paragraph (g)(2)(ii) of this AD was accomplished. BILLING CODE 4910-13-P ER08MR18.000 ER08MR18.001 ER08MR18.002 BILLING CODE 4910-13-C
Unsafe condition
This AD was prompted by seven low-time loss-of-thrust-control events attributed to water intrusion of the engine ECU. We are issuing this AD to prevent a dual engine power loss. The unsafe condition, if not addressed, could result in loss of thrust control, damage to the engine, and damage to the airplane.
Affected ADs
None.
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