Airworthiness directives › 2016-22-16
AD 2016-22-16 Airworthiness Directives; Bombardier, Inc. Airplanes
Applicability*9
This AD applies to the Bombardier, Inc. airplanes identified in paragraph (c)(1), (c)(2), or (c)(3) of this AD, certificated in any category, equipped with No. 3 hydraulic system reservoir having part number 960450-1. (1) Model CL-600-2C10 (Regional Jet Series 700, 701, and 702) airplanes, having serial numbers 10002 through 10999 inclusive. (2) Model CL-600-2D15 (Regional Jet Series 705) and CL-600-2D24 (Regional Jet Series 900) airplanes, having serial numbers 15001 through 15990 inclusive. (3) Model CL-600-2E25 (Regional Jet Series 1000) airplanes, having serial numbers 19001 through 19990 inclusive.
Compliance
Comply with this AD within the compliance times specified, unless already done.
Required actions
Within 660 flight hours or 4 months after the effective date of this AD, whichever occurs first: Perform an operational check for wear and leakage of the high-pressure seal in the cylinder of the reservoir of the No. 3 hydraulic system, in accordance with the Accomplishment Instructions of Bombardier Service Bulletin 670BA-29-018, Revision A, dated October 13, 2015. If the operational check fails, before further flight, do applicable corrective actions and repeat the operational check and applicable corrective actions until the operational check passes. Repeat the operational check thereafter at intervals not to exceed 660 flight hours or 4 months, whichever occurs first.
Unsafe condition
This AD was prompted by a determination that wear and possible leakage of the high-pressure seal in the cylinder of the No. 3 hydraulic system reservoir could occur and cause high hydraulic fluid temperature and/or prevent the system from reaching normal operating pressure. We are issuing this AD to detect and correct wear and leakage of the high-pressure seal in the cylinder of the reservoir of the No. 3 hydraulic system, which can result in high hydraulic fluid temperature. High hydraulic fluid temperature combined with a temperature transducer malfunction could result in un-annunciated overheating of the hydraulic system and consequent ignition sources inside the fuel tank, which, combined with flammable fuel vapors, could result in a fuel tank explosion and consequent loss of the airplane.
Affected ADs
None.
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