Airworthiness Directive · Amendment 39-11768 · Bombardier Model DHC-8-100 and -300 Series Airplanes
Bombardier Model DHC-8-100 and -300 Series Airplanes
Model DHC-8-100 and -300 series airplanes, serial numbers 215 through 341 inclusive; certificated in any category.
Note 1: This AD applies to each airplane identified in the preceding applicability provision, regardless of whether it has been modified, altered, or repaired in the area subject to the requirements of this AD. For airplanes that have been modified, altered, or repaired so that the performance of the requirements of this AD is affected, the owner/operator must request approval for an alternative method of compliance in accordance with paragraph (e) of this AD. The request should include an assessment of the effect of the modification, alteration, or repair on the unsafe condition addressed by this AD; and, if the unsafe condition has not been eliminated, the request should include specific proposed actions to address it.
This amendment adopts a new airworthiness directive (AD), applicable to certain Bombardier Model DHC-8-100 and -300 series airplanes, that requires revising the Aircraft Log Book to correct the airplane Production Modification List; performing an inspection to determine which bonded skin panels on the airplane require bonding integrity inspections (BII); and revising the Airworthiness Limitations List of the Approved Maintenance Plan to include the BII requirements. This amendment also requires, for certain airplanes, repetitive ultrasonic bond inspections to detect disbonding of airplane skin panels, and repair, if necessary. This amendment is prompted by issuance of mandatory continuing airworthiness information by a foreign civil airworthiness authority. The actions specified by this AD are intended to prevent damage to bonded skin panels to go undetected, which could result in failure of the bonded skin panels, and consequent loss of controllability of the airplane.
To prevent damage to bonded skin panels to go undetected, which could result in failure of the bonded skin panels, and consequent loss of controllability of the airplane, accomplish the following:
(a) Within 30 days after the effective date of this AD, perform the actions required by paragraphs (a)(1), (a)(2), and (a)(3) of this AD.
(1) Revise the Aircraft Log Book to correct the airplane Production Modification List in accordance with the Accomplishment Instructions in Part A of Section III of Bombardier Service Bulletin S.B. 8-51-2, Revision ‘A,’ dated September 19, 1998.
(2) Perform an inspection to determine which bonded skin panels on the airplane require bonding integrity inspections (BII) in accordance with the Accomplishment Instructions in Part B of Section III of Bombardier Service Bulletin S.B. 8-51-2, Revision ‘A,’ dated September 19, 1998.
(3) Revise the Airworthiness Limitations List of the Approved Maintenance Plan by inserting the bonding integrity inspections identified as de Havilland Maintenance Task 5500/01 and de Havilland Maintenance Task 5700/01 into the Airworthiness Limitations List. Except as provided by paragraph (e) of this AD: After the actions specified in paragraph (a)(3) of this AD have been accomplished, no alternative replacement times or structural inspection intervals may be approved for the bonded panels of the empennage and wings specified in de Havilland Maintenance Task 5500/01 and de Havilland Maintenance Task 5700/01.
(b) For airplanes on which the bonded skin panels require BII's, as determined in paragraph (a)(2) of this AD: At the next required maintenance visit, but no later than 12 months after the effective date of this AD, perform an initial ultrasonic bond inspection to detect disbonding of the skin panels, in accordance with Part 5, sections 55-00-01 and/or 57-30-01, of Bombardier Production Support Manual (PSM) 1-8-7A, dated December 15, 1998 (for Model DHC-8-100 series airplanes); or Part 5, sections 55-00-01 and 57-30-01 of Bombardier PSM 1-83-7A, dated April 30, 1999 (for Model DHC-8-300 series airplanes); as applicable. Thereafter, repeat the ultrasonic inspection at the interval specified in the applicable PSM.
(c) Except as provided by paragraph (d) of this AD, if any disbonding is detected during any inspection required by paragraph (b) of this AD, prior to further flight, repair in accordance with Part 5, sections 55-00-01 and 57-30-01 of Bombardier PSM 1-8-7A, dated December 15, 1998 (for Model DHC-8-100 series airplanes); or Part 5, sections 55-00-01 and 57-30-01 of Bombardier PSM 1-83-7A, dated April 30, 1999 (for Model DHC-8-300 series airplanes); as applicable.
(d) If any disbonding is detected during any inspection required by paragraph (b) of this AD; and the applicable service information specifies to contact Bombardier for appropriate action: Prior to further flight, repair in accordance with a method approved by the Manager, New York Aircraft Certification Office (ACO), FAA, Engine and Propeller Directorate. For a repair method to be approved by the Manager, New York ACO, as required by this paragraph, the Manager's approval letter must specifically reference this AD.
