AD 2011-17-17

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 airplanes having S/Ns 003, 004, 006, and 008 through 182 inclusive (now referred to as S/Ns 4003, 4004, 4006, and 4008 through 4182 inclusive), before further flight, do a general visual inspection to detect discrepancies of the left- and right-hand MLG system and do all applicable corrective actions, in accordance with a method approved by the Manager, New York Aircraft Certification Office (ACO), FAA; or Transport Canada Civil Aviation (TCCA) (or its delegated agent).

Note 1: For the purposes of this AD, a general visual inspection is: “A visual examination of an interior or exterior area, installation, or assembly to detect obvious damage, failure, or irregularity. This level of inspection is made from within touching distance unless otherwise specified. A mirror may be necessary to ensure visual access to all surfaces in the inspection area. This level of inspection is made under normally available lighting conditions such as daylight, hangar lighting, flashlight, or droplight and may require removal or opening of access panels or doors. Stands, ladders, or platforms may be required to gain proximity to the area being checked.”

Note 2: Guidance on doing a general visual inspection to detect discrepancies of the left- and right-hand MLG system can be found in Tasks Z700-03E and Z700-04E of Part 1 (Maintenance Review Board Report) of the Bombardier DHC-8 Series 400 Maintenance Requirements Manual (PSM 1-84-7).

For all airplanes except for the airplane having serial number 4001: Before further flight, do a general visual inspection of the jam nut of the retract actuator of the left- and right-hand MLG to ensure the wire lock is in place and the nut is secured. If the wire lock is not in place or if the jam nut is not secured, before further flight, adjust the retracted length of the rod end, torque the jam nut, install a wire lock, and lubricate the piston, as applicable, in accordance with Bombardier Repair Drawing (RD) 8/4-32-059, Issue 4, dated September 14, 2007; or Issue 7, dated June 26, 2008. As of the effective date of this AD, use only Bombardier RD 8/4-32-059, Issue 7, dated June 26, 2008. Doing the revision required by paragraph (r) of this AD terminates the inspection required by this paragraph.

Note 3: Bombardier RD 8/4-32-059, Issue 4, dated September 14, 2007, refers to Goodrich Service Concession Request SCR 086-07, Revision C, dated September 14, 2007 (specifically item 14); and Bombardier RD 8/4-32-059, Issue 7, dated June 26, 2008, refers to Goodrich Service Concession Request SCR 086-07, Revision F, dated June 13, 2008 (specifically item 14); as an additional source of service information for adjusting the retracted length of the rod end, torquing the jam nut, installing a wire lock, and lubricating the piston if necessary, as required by paragraph (h) of this AD.

(i) For airplanes having S/Ns 003, 004, 006, and 008 through 182 inclusive (now referred to as S/Ns 4003, 4004, 4006, and 4008 through 4182 inclusive) on which the retract actuator of the MLG, part number (P/N) 46550-7 or 46550-9, has accumulated 8,000 or more total landings or has been in-service 4 or more years since new, as of November 14, 2007 (the effective date of AD 2007-22-09, Amendment 39-15245 (72 FR 61288, October 30, 2007)): Before further flight, do a detailed inspection of affected parts for any signs of corrosion or wear, and applicable related investigative and corrective actions, in accordance with Bombardier RD 8/4-32-059, Issue 4, dated September 14, 2007; or Issue 7, dated June 26, 2008. As of the effective date of this AD, use only Bombardier RD 8/4-32-059, Issue 7, dated June 26, 2008.

Note 4: For the purposes of this AD, a detailed inspection is: “An intensive examination of a specific item, installation, or assembly to detect damage, failure, or irregularity. Available lighting is normally supplemented with a direct source of good lighting at an intensity deemed appropriate. Inspection aids such as mirror, magnifying lenses, etc., may be necessary. Surface cleaning and elaborate procedures may be required.”

(j) For airplanes having S/Ns 003, 004, 006, and 008 through 182 inclusive (now referred to as S/Ns 4003, 4004, 4006, and 4008 through 4182 inclusive) with a retract actuator of the MLG, P/N 46550-7 or 46550-9, other than those identified in paragraph (i) of this AD: Do a detailed inspection of affected parts for any signs of corrosion or wear, and applicable related investigative and corrective actions, in accordance with Bombardier RD 8/4-32-059, Issue 4, dated September 14, 2007; or Issue 7, dated June 26, 2008; at the later of the times specified in paragraphs (j)(1) and (j)(2) of this AD. As of the effective date of this AD, use only Bombardier RD 8/4-32-059, Issue 7, dated June 26, 2008.

(1) Before the accumulation of 4,500 total landings or 27 months since new, whichever occurs first.

(2) Within 500 flight hours after November 14, 2007, or within 3 months after the effective date of this AD, whichever occurs first.

Note 5: Bombardier RD 8/4-32-059, Issue 7, dated June 26, 2008, refers to Goodrich Service Concession Request SCR 086-07, Revision F, dated June 13, 2008, as an additional source of service information for accomplishing the applicable related investigative and corrective actions required by paragraphs (i) and (j) of this AD.

Actions done before November 14, 2007, in accordance with repair drawings specified in Table 1 of this AD, are acceptable for compliance with the corresponding actions specified in paragraphs (h) through (j) of this AD.

For all airplanes: At the later of the times specified in paragraphs (l)(1) and (l)(2) of this AD, do a general visual inspection of the left- and right-hand MLG retract actuator jam nut to ensure that the wire lock is in place and that the nut is secure, in accordance with a method approved by the Manager, New York ACO, FAA; or TCCA (or its delegated agent). If the wire lock is not in place or the jam nut is not secured, before further flight, re-torque the jam nut and safety lockwire, in accordance with Bombardier RD 8/4-32-059, Issue 7, dated June 26, 2008. Repeat the inspection thereafter at intervals not to exceed 250 flight cycles or 30 days, whichever occurs first. Doing the revision required by paragraph (r) of this AD terminates the inspections required by this paragraph.

(1) Within 250 flight cycles or 30 days after accomplishing the inspection required by paragraph (h) of this AD, whichever occurs first.

(2) Within 7 days after the effective date of this AD.

Note 6: Guidance for doing a general visual inspection to detect discrepancies of the left- and right-hand MLG system can be found in Tasks Z700-03E and Z700-04E of Part 1 (Maintenance Review Board Report) of the Bombardier DHC-8 Series 400 Maintenance Requirements Manual (PSM 1-84-7).

For airplanes equipped with a MLG retract actuator having P/N 46550-7 or 46550-9: At the later of the times specified in paragraphs (m)(1) and (m)(2) of this AD, do a detailed inspection of affected parts for any signs of corrosion or wear, and do applicable related investigative and corrective actions, in accordance with Bombardier RD 8/4-32-059, Issue 7, dated June 26, 2008. Do all applicable related investigative and corrective actions before further flight. Repeat the inspection thereafter at intervals not to exceed 2,000 flight cycles or 12 months, whichever occurs first.

(1) Within 2,000 flight cycles or within 12 months after accomplishing the inspection required by paragraph (i) or (j) of this AD, whichever occurs first.

(2) Within 30 days after the effective date of this AD.

(n) For airplanes having serial numbers 4001, 4003, 4004, 4006, and 4008 through 4182 inclusive equipped with a MLG retract actuator having P/N 46550-11: At the later of the times specified in paragraphs (n)(1) and (n)(2) of this AD, do a detailed inspection of affected parts for any signs of corrosion or wear, and applicable related investigative and corrective actions, in accordance with Bombardier RD 8/4-32-059, Issue 7, dated June 26, 2008. Do all applicable related investigative and corrective actions before further flight. Repeat the inspection thereafter at intervals not to exceed 2,000 flight cycles or 12 months, whichever occurs first.

(1) Before the accumulation of 4,500 total landings or 27 months since new, whichever occurs first.

(2) Within 500 flight hours or 3 months after the effective date of this AD, whichever occurs first.

(o) For airplanes having serial numbers 4001, 4003, 4004, 4006, and 4008 through 4182 inclusive equipped with a MLG retract actuator having P/N 46550-7, P/N 46550-9, or P/N 46550-11, and that have accumulated 7,500 total flight cycles or more as of the effective date of this AD, or that have more than 48 months since new: Within 500 flight cycles or 3 months after the effective date of this AD, whichever occurs first, replace the affected retract actuator with a new design retract actuator having P/N 46550-13, in accordance with Bombardier Service Bulletin 84-32-55, Revision A, dated March 10, 2008 (Bombardier Modsum 4-901603). Doing the replacement specified in this paragraph terminates the requirements of paragraphs (i), (j), (m), and (n) of this AD.

(p) For airplanes having serial numbers 4001, 4003, 4004, 4006, and 4008 through 4182 inclusive equipped with MLG retract actuators having P/N 46550-7, P/N 46550-9, or P/N 46550-11, that have accumulated less than 7,500 total flight cycles as of the effective date of this AD and that have 48 months or less since new: Prior to the accumulation of 8,000 total flight cycles, or within 51 months since new, whichever occurs first, replace the affected retract actuator with a new design retract actuator having P/N 46550-13, in accordance with Bombardier Service Bulletin 84-32-55, Revision A, dated March 10, 2008 (Bombardier Modsum 4-901603). Doing the replacement specified in this paragraph terminates the requirements of paragraphs (i), (j), (m), and (n) of this AD.

(q) Replacing the affected retract actuator with a new design retract actuator having P/N 46550-15, in accordance with the Accomplishment Instructions of Bombardier Service Bulletin 84-32-60, Revision A, dated September 29, 2008 (Bombardier Modsum 4-901610), is also acceptable for compliance with the requirements of paragraphs (o) and (p) of this AD.

For all airplanes: Within 30 days after the effective date of this AD, revise the maintenance program by incorporating Task 320100-211 (repetitive detailed inspections of the retraction actuator rod end jam nut, gland nut, and actuator attachment pins for condition, the security of installation, and corrosion) and Task 320100-212 (repetitive restorations of the retraction actuator for complete overhaul), as specified in Bombardier Temporary Revision (TR) MRB-35, dated November 18, 2008, to the Bombardier Q400 Dash 8 Maintenance Requirements Manual (PSM 1-84-7). Doing this revision terminates the requirements of paragraphs (h) and (l) of this AD. The initial compliance times for doing Task 320100-211 and Task 320100-212 are specified in paragraphs (r)(1) and (r)(2) of this AD. After doing this revision, no alternative inspections, restorations, or intervals may be used, unless the inspections, restorations, or intervals are approved as an alternative method of compliance (AMOC) in accordance with the procedures specified in paragraph (v)(1) of this AD.

(1) For Task 320100-211 in Bombardier TR MRB-35, dated November 18, 2008, to the Bombardier Q400 Dash 8 Maintenance Requirements Manual (PSM 1-84-7): The compliance time for the initial inspection is within 600 flight hours after the effective date of this AD.

(2) For Task 320100-212 in Bombardier TR MRB-35, dated November 18, 2008, to the Bombardier Q400 Dash 8 Maintenance Requirements Manual (PSM 1-84-7): The compliance time for the initial restoration is the later of the times of paragraphs (r)(2)(i) and (r)(2)(ii) of this AD.

(i) Prior to the accumulation of 25,000 total flight cycles, or within 12 years since the date of issuance of the original airworthiness certificate or the date of issuance of the original export certificate of airworthiness, whichever occurs first.

(ii) Within 500 flight cycles after the effective date of this AD.

Note 7: The actions required by paragraph (r) of this AD may be done by inserting copies of Bombardier TR MRB-35, dated November 18, 2008, into the Bombardier Q400 Dash 8 Maintenance Requirements Manual (PSM 1-84-7). When this TR has been included in general revisions of the PSM, the general revisions may be inserted in the PSM, provided the relevant information in the general revision is identical to that in Bombardier TR MRB-35, dated November 18, 2008.

Doing a general visual inspection of the jam nut of the retract actuator of the left- and right-hand MLG; and doing a detailed inspection of affected parts for any signs of corrosion or wear, and applicable related investigative and corrective actions; is also acceptable for compliance with the corresponding requirements of paragraphs (h), (i), (j), (l), (m), and (n) of this AD, if done before the effective date of this AD in accordance with Bombardier Repair Drawing 8/4-32-059, Issue 5, dated September 20, 2007; or Bombardier Repair Drawing 8/4-32-059, Issue 6, dated January 31, 2008.

(t) Replacing the affected retract actuator with a new design retract actuator having P/N 46550-13 is also acceptable for compliance with the requirements of paragraphs (o) and (p) of this AD, if done before the effective date of this AD in accordance with Bombardier Service Bulletin 84-32-55, dated January 14, 2008 (Modsum 4-901603).

While Canadian Airworthiness Directive CF-2007-20R2, dated February 6, 2009, has a reporting action, this AD does not require reporting.

Note 8: This AD differs from the MCAI and/or service information as follows: Although the MCAI or service information tells you to submit information to the manufacturer, paragraph (u) of this AD specifies that such submittal is not required.