Airworthiness directives › 2020-11-13
AD 2020-11-13 July 14, 2020 Airworthiness Directives; De Havilland Aircraft of Canada Limited (Type Certificate Previously Held by Bombardier, Inc.) Airplanes
Models named: DHC-8-400, -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-8-400, -401, and -402 airplanes, certificated in any category, serial numbers 4001 and subsequent.
Compliance
Comply with this AD within the compliance times specified, unless already done.
Required actions
This paragraph restates the requirements of paragraph (g) of AD 2010-23-04, with revised service information and revised replacement instructions. For airplanes having serial numbers 4001 through 4304 inclusive, 4314, and 4315: Within 100 flight hours after November 22, 2010 (the effective date of AD 2010-23-04), do a detailed inspection for cracking, and a conductivity inspection on each of the 4 nacelle attachment fittings, in accordance with the Accomplishment Instructions of Bombardier Service Bulletin 84-54-14, Revision K, dated August 7, 2018. Repeat the detailed inspection at intervals not to exceed 300 flight hours, except as provided by paragraph (i) of this AD. Accomplishing the replacement specified in paragraph (g)(1)(ii) or (g)(2)(ii)(B) of this AD terminates the inspections required by this paragraph. (1) If any nacelle attachment fitting is found cracked, before further flight, do the action specified in paragraph (g)(1)(i) or (ii) of this AD. As of the effective date of this AD, only the action specified in paragraph (g)(1)(ii) of this AD may be done. (i) Replace the fitting with a new fitting in accordance with paragraph (2) of Part A of the Accomplishment Instructions of Bombardier Service Bulletin 84-54-14, Revision K, dated August 7, 2018. (ii) Replace the rear spar nacelle attachment fitting and associated structure with a new nacelle attachment fitting, part number (P/N) 8Z9305, and do all applicable related investigative and corrective actions, in accordance with Part B of the Accomplishment Instructions of Bombardier Service Bulletin 84-54-16 Revision D, dated August 7, 2018. Do all applicable related investigative and corrective actions before further flight. (2) If the conductivity of any test points on any fitting is found to be greater than 45.0 percent International Annealed Copper Standard (IACS) or if the conductivity of any test points on any fitting is found to be less than 38.0 percent IACS, do the actions required by paragraphs (g)(2)(i) and (ii) of this AD. (i) Within 24 hours after accomplishing the conductivity inspection specified in paragraph (g) of this AD, do a detailed inspection of the nacelle attachment fitting for cracking, in accordance with the Accomplishment Instructions of Bombardier Service Bulletin 84-54-14, Revision K, dated August 7, 2018, and repeat thereafter at intervals not to exceed 24 hours. If cracking is found, before further flight, replace the fitting with a new fitting in accordance with the requirements of paragraph (g)(2)(ii) of this AD. Replacement of the fitting terminates the daily detailed inspection requirements of this paragraph. (ii) Except as required by paragraph (g)(2)(i) of this AD: Within 300 flight hours after accomplishing the conductivity inspection specified in paragraph (g) of this AD, do the action specified in paragraph (g)(2)(ii)(A) or (B) of this AD. As of the effective date of this AD, only the action specified in paragraph (g)(2)(ii)(B) of this AD may be done. (A) Replace the fitting with a new fitting in accordance with paragraph (2) of Part A of the Accomplishment Instructions of Bombardier Service Bulletin 84-54-14, Revision K, dated August 7, 2018. (B) Replace the rear spar nacelle attachment fitting and associated structure with a new nacelle attachment fitting, P/N 8Z9305, and do all applicable related investigative and corrective actions, in accordance with Part B of the Accomplishment Instructions of Bombardier Service Bulletin 84-54-16 Revision D, dated August 7, 2018. Do all applicable related investigative and corrective actions before further flight.
Unsafe condition
This AD was prompted by reports of cracked nacelle attachment fittings, which a preliminary investigation determined to be caused by stress corrosion. The FAA is issuing this AD to address this condition, which, if not detected and corrected, could compromise the structural integrity of the nacelle attachment fitting and possibly result in collapse of the landing gear.
Affected ADs
This AD replaces AD 2010-23-04, Amendment 39-16493 (75 FR 68174, November 5, 2010) (“AD 2010-23-04”).
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