Airworthiness Directive · Amendment 39-16756 · Landing gear
Bombardier, Inc. Model DHC-8-400 Series Airplanes
Superseded. A later AD replaced this one: AD 2014-16-07. Comply with the one in force.
This AD applies to Bombardier, Inc. Model DHC-8-400, -401, and -402 airplanes, certificated in any category, serial numbers 4001 and subsequent.
We are adopting a new airworthiness directive (AD) for the products listed above that would supersede an existing AD. This AD results from mandatory continuing airworthiness information (MCAI) originated by an aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as:
You are responsible for having the actions required by this AD performed within the compliance times specified, unless the actions have already been done.
Within 50 flight hours or 10 days after March 25, 2011 (the effective date of AD 2011-05-14), whichever occurs first, do a detailed inspection for proper operation of the MLG AES cam mechanism, in accordance with paragraph A) of Bombardier Repair Drawing 8/4-32-0160, Issue 2, dated January 18, 2011; or Issue 3, dated February 15, 2011. Repeat the inspection thereafter at intervals not to exceed 50 flight hours or 10 days, whichever occurs first, until the inspection required by paragraph (i) of this AD is accomplished.
(1) If the cam mechanism is found to reset to the normal rested position without any sticking or binding, it is operating properly.
(2) If the cam mechanism has not reset to its normal rested position, or if any sticking or binding is observed, before further flight, remove the cam assembly, in accordance with paragraph A) of Bombardier Repair Drawing 8/4-32-0160, Issue 2, dated January 18, 2011; or Issue 3, dated February 15, 2011; and do the actions in paragraph (g)(2)(i) or (g)(2)(ii) of this AD.
(i) Repair the cam mechanism assembly, including doing detailed inspections for discrepancies (including an inspection to determine proper operation, an inspection for damage, an inspection for corrosion and cadmium coating degradation, and inspections to determine dimensions are within the limits specified in paragraph B) of Bombardier Repair Drawing 8/4-32-0160, Issue 2, dated January 18, 2011; or Issue 3, dated February 15, 2011), in accordance with paragraph B) of Bombardier Repair Drawing 8/4-32-0160, Issue 2, dated January 18, 2011; or Issue 3, dated February 15, 2011; and install the repaired cam assembly in accordance with paragraph C) of Bombardier Repair Drawing 8/4-32-0160, Issue 2, dated January 18, 2011; or Issue 3, dated February 15, 2011.
(ii) Install a new or serviceable cam assembly, in accordance with paragraph C) of Bombardier Repair Drawing 8/4-32-0160, Issue 2, dated January 18, 2011; or Issue 3, dated February 15, 2011.
(3) If the cam mechanism is found damaged or inoperative during the repair specified in paragraph (g)(2)(i) of this AD, or if any discrepancies are found and Bombardier Repair Drawing 8/4-32-0160, Issue 2, dated January 18, 2011; or Issue 3, dated February 15, 2011; does not specify repairs for those discrepancies, or repairs specified in paragraph (g)(2)(i) of this AD cannot be accomplished: Before further flight, repair and reinstall using a method approved by the Manager, ANE-170, New York Aircraft Certification Office (ACO), FAA, or Transport Canada Civil Aviation (TCCA) (or its delegated agent); or install a new or serviceable cam assembly, in accordance with paragraph C) of Bombardier Repair Drawing 8/4-32-0160, Issue 2, dated January 18, 2011; or Issue 3, dated February 15, 2011.
Actions done before March 25, 2011, in accordance with Bombardier 8/4-32-0160, Issue 1, dated January 14, 2011, are acceptable for compliance with the corresponding requirements of this AD.
(i) Within 50 flight hours or 10 days after the effective date of this AD, whichever occurs first, do a detailed inspection for proper operation of the MLG AES cam mechanism, in accordance with paragraph A) of Bombardier Repair Drawing 8/4-32-0160, Issue 3, dated February 15, 2011. Repeat the inspection thereafter at intervals not to exceed 50 flight hours or 10 days, whichever occurs first. Accomplishing this inspection terminates the requirements of paragraph (g) of this AD.
(1) If the cam mechanism is found to reset to the normal rested position without any sticking or binding, it is operating properly.
(2) If the cam mechanism has not reset to its normal rested position, or if any sticking or binding is observed, before further flight, remove the cam assembly, in accordance with paragraph A) of Bombardier Repair Drawing 8/4-32-0160, Issue 3, dated February 15, 2011, and do the actions in paragraph (i)(2)(i) or (i)(2)(ii) of this AD.
(i) Repair the cam mechanism assembly, including doing detailed inspections for discrepancies (including an inspection to determine proper operation, an inspection for damage, an inspection for corrosion and cadmium coating degradation, and inspections to determine dimensions are within the limits specified in paragraph B) of Bombardier Repair Drawing 8/4-32-0160, Issue 3, dated February 15, 2011), in accordance with paragraph B) of Bombardier Repair Drawing 8/4-32-0160, Issue 3, dated February 15, 2011; and install the repaired cam assembly in accordance with paragraph C) of Bombardier Repair Drawing 8/4-32-0160, Issue 3, dated February 15, 2011.
(ii) Install a new or serviceable cam assembly, in accordance with paragraph C) of Bombardier Repair Drawing 8/4-32-0160, Issue 3, dated February 15, 2011.
(3) If the cam mechanism is found damaged or inoperative during the repair specified in paragraph (i)(2)(i) of this AD, or if any discrepancies are found and Bombardier Repair Drawing 8/4-32-0160, Issue 3, dated February 15, 2011, does not specify repairs for those discrepancies, or repairs specified in paragraph (i)(2)(i) of this AD cannot be accomplished: Before further flight, repair and reinstall using a method approved by the Manager, ANE-170, New York Aircraft Certification Office (ACO), FAA, or Transport Canada Civil Aviation (TCCA) (or its delegated agent); or install a new or serviceable cam assembly, in accordance with paragraph C) of Bombardier Repair Drawing 8/4-32-0160, Issue 3, dated February 15, 2011.
Note 1: This AD differs from the MCAI and/or service information as follows: No differences.
