Airworthiness directives › 2019-24-12
AD 2019-24-12 Airworthiness Directives; De Havilland Aircraft of Canada Limited (Type Certificate Previously Held by Bombardier, Inc.) Airplanes
Models named: DHC-8-401, -402. Read the applicability below — it usually turns on serial or part numbers too.
Applicability*9
This AD applies to De Havilland Aircraft of Canada Limited (Type Certificate Previously Held by Bombardier, Inc.) Model DHC-8-401 and -402 airplanes, certificated in any category, serial numbers 4327, 4330, 4337, 4342, 4350, 4352, 4362, 4367, 4372, 4375, 4376, 4378, 4383, 4384, 4385, 4388, 4391, 4392, 4396, and 4397.
Compliance
Comply with this AD within the compliance times specified, unless already done.
Required actions
Within 8,000 flight hours or 5 years after the effective date of this AD, whichever occurs first: Do a detailed visual inspection of the stringer end fittings and keel fittings at fuselage stations X373.15 and X428.50 for loose and working fasteners, signs of wear, and corrosion in accordance with paragraph 3.B. of the Accomplishment Instructions of De Havilland Aircraft of Canada Limited Service Bulletin 84-53-75, Revision A, dated August 2, 2019. If any loose or working fasteners, signs of wear, or corrosion are found during any inspection required by this paragraph, before further flight, repair using a method approved by the Manager, New York ACO Branch, FAA; or Transport Canada Civil Aviation (TCCA); or De Havilland Aircraft of Canada Limited's TCCA Design Approval Organization (DAO). If approved by the DAO, the approval must include the DAO-authorized signature. Doing the actions specified in Bombardier Service Bulletin 84-53-66 does not constitute compliance with the actions specified in this paragraph.
Unsafe condition
This AD was prompted by a report that certain fuselages were delivered with non-conforming keel tension fittings and stringer end fittings. The FAA is issuing this AD to address non-conforming keel tension fittings and stringer end fittings which could lead to premature cracking and corrosion in several locations and compromise the structural integrity of the fuselage joints.
Affected ADs
None.
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