Airworthiness Directive · Amendment 39-16356 · Landing gear
Bombardier, Inc. Model DHC-8-400 Series Airplanes
This AD applies to Bombardier, Inc. Model DHC-8-400, -401, and -402 airplanes, having serial numbers (S/Ns) 4001, 4003, 4004, 4006, and 4008 through 4227 inclusive, certificated in any category.
Note 1: This AD requires revisions to certain operator maintenance documents to include new inspections. Compliance with these inspections is required by 14 CFR 91.403(c). For airplanes that have been previously modified, altered, or repaired in the areas addressed by these inspections, the operator may not be able to accomplish the inspections described in the revisions. In this situation, to comply with 14 CFR 91.403(c), the operator must request approval for an alternative method of compliance according to paragraph (j)(1) of this AD. The request should include a description of changes to the required inspections that will ensure the continued damage tolerance of the affected structure. The FAA has provided guidance for this determination in Advisory Circular (AC) 25.1529-1A.
We are adopting a new airworthiness directive (AD) for the products listed above. 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.
For Model DHC-8-400, -401, and -402 airplanes having S/Ns 4001, 4003, 4004, 4006, and 4008 through 4210 inclusive: Do the actions specified in paragraphs (g)(1) and (g)(2) of this AD.
(1) Within 60 days after the effective date of this AD: Revise the ALS of the Instructions for Continued Airworthiness by incorporating the revised structural safe life limit for the upper bearing having part number (P/N) 46114-1, as provided in Bombardier Temporary Revision (TR), ALI-82, dated August 15, 2008, to Part 2, Airworthiness Limitation Items, of the Bombardier Dash 8 Q400 Maintenance Requirements Manual (MRM), PSM 1-84-7. The initial compliance time for replacing the upper bearing is specified in paragraph (g)(2) of this AD.
(2) Replace the upper bearing having P/N 46114-1 with a new or serviceable upper bearing, in accordance with Goodrich Dressed Shock Strut Assembly Main Landing Gear Part No. 46100-29/-31/-33/-35/-37/-39/-41/-43/-45/-47/-49/-51/-53 and -55 Component Maintenance Manual with Illustrated Parts List 32-11-03, Revision 11, dated August 22, 2008, at the applicable time specified in paragraphs (g)(2)(i), (g)(2)(ii), and (g)(2)(iii), of this AD.
(i) For airplanes having accumulated fewer than 15,000 total flight cycles as of the effective date of this AD: Replace prior to the accumulation of 15,000 total flight cycles.
(ii) For airplanes having accumulated 15,000 total flight cycles or more, but fewer than 20,000 total flight cycles, as of the effective date of this AD: Replace prior to the accumulation of 20,000 total flight cycles.
(iii) For airplanes having accumulated 20,000 total flight cycles or more as of the effective date of this AD: Replace before further flight.
(h) For Model DHC-8-400, -401, and -402 series airplanes having S/Ns 4001, 4003, 4004, 4006, and 4008 through 4227 inclusive: Do the applicable actions specified in paragraphs (h)(1) and (h)(2) of this AD.
(1) Within 60 days after the effective date of this AD: Revise the ALS of the Instructions for Continued Airworthiness to incorporate the revised safe life limits for the retraction actuator assembly rod end having P/N P3A2750 and P3A2750-1; retraction actuator assembly piston having P/N 46570-5; lock actuator cylinder assembly having P/N 46601-1/-3; and lock actuator assembly having P/N 46600-1/-3/-5/-7; as provided in Bombardier TR ALI-89, dated March 27, 2009, to Part 2, Airworthiness Limitation Items, of the Bombardier Dash 8 Q400 MRM, PSM 1-84-7. The initial compliance time for the replacement is specified in the TR, except as provided by paragraph (h)(2) of this AD.
(2) For airplanes with a main landing gear retraction actuator assembly rod end that has accumulated more than 9,850 total flight cycles as of the effective date of this AD: Within 600 flight cycles after the effective date of this AD, replace any affected rod end having P/Ns P3A2750 and P3A2750-1 with a new or serviceable rod end, in accordance with Goodrich Dressed Shock Strut Assembly Main Landing Gear Part No. 46100-29/-31/-33/-35/-37/-39/-41/-43/-45/-47/-49/-51/ -53 and -55 Component Maintenance Manual with Illustrated Parts List 32-11-03, Revision 11, dated August 22, 2008.
(i) After accomplishing the revision specified in paragraph (g)(1) or (h)(1) of this AD, except as provided in paragraph (j) of this AD, no alternative replacement times may be approved for this part.
Note 2: The ALI revisions required by paragraphs (g) and (h) of this AD may be done by inserting copies of Bombardier TRs ALI-82 and ALI-89 into Part 2, Airworthiness Limitation Items, of the Bombardier Dash 8 Q400 MRM, PSM 1-84-7. When these TRs have been included in the general revision of the MRM, the general revision may be inserted into the MRM, provided the relevant information in the general revision is identical to that in Bombardier TRs ALI-82 and ALI-89.
Note 3: This AD differs from the MCAI and/or service information as follows: The MCAI and service information do not contain replacement procedures for the upper bearings and rod ends. This AD requires replacing the upper bearings and rod ends in accordance with Goodrich Dressed Shock Strut Assembly Main Landing Gear Part No. 46100-29/-31/-33/-35/-37/-39/-41/-43/-45/-47/-49/-51/-53 and -55 Component Maintenance Manual with Illustrated Parts List 32-11-03, Revision 11, dated August 22, 2008.
