Airworthiness Directive · Amendment 39-19625 · Fuselage
Bombardier, Inc., Airplanes
This AD applies to Bombardier, Inc., Model CL-600-2B19 (Regional Jet Series 100 & 440) airplanes, certificated in any category, serial numbers 7002 through 8025 inclusive, 8030, and 8034.
We are superseding Airworthiness Directive (AD) 2012-25-02, which applied to certain Bombardier, Inc., Model CL-600-2B19 (Regional Jet Series 100 & 440) airplanes. AD 2012-25-02 required revising the airworthiness limitations section (AWL) of the instructions for continued airworthiness (ICA) of the maintenance requirements manual (MRM) by incorporating new procedures for repetitive inspections for cracking of the rear pressure bulkhead (RPB). AD 2012-25-02 also required revising the maintenance or inspection program to incorporate a revised task. This AD also mandates modification of the RPB and adds repetitive inspections for cracking of the RPB web, which terminates certain actions in this AD. This AD was prompted by additional in- service crack findings, which resulted in the development of a structural modification to the RPB. We are issuing this AD to address the unsafe condition on these products.
This paragraph restates the requirements of paragraph (i) of AD 2012-25-02, with minor changes. Except for the airplane having serial number 7002, within 60 days after January 16, 2013 (the effective date of AD 2012-25-02): Revise the maintenance program by incorporating the revised inspection requirements specified in airworthiness limitation section (AWL) 53-61-153 of Bombardier temporary revision (TR) 2B-2187, dated June 22, 2011, to Appendix B-Airworthiness Limitations, of Part 2 of the Bombardier CL-600-2B19 Maintenance Requirements Manual (MRM). The initial compliance times for the task are at the applicable time specified in paragraph (g)(1) or (g)(2) of this AD.
(1) For airplanes on which the special detailed inspection specified in AWL 53-61-153 of Bombardier TR 2B-2187, dated June 22, 2011; or Canadair Regional Jet TR 2B-2109, dated October 13, 2005; has not been done as of January 16, 2013 (the effective date of AD 2012-25-02): The initial compliance time for AWL 53-61-153 is at the applicable time specified in paragraph (g)(1)(i) or (g)(1)(ii) of this AD.
(i) For airplanes that have accumulated 10,500 total flight cycles or less as of January 16, 2013: Before the accumulation of 12,000 total flight cycles.
(ii) For airplanes that have accumulated more than 10,500 total flight cycles as of January 16, 2013: Within 1,500 flight cycles after January 16, 2013 (the effective date of AD 2012-25-02).
(2) For airplanes on which the special detailed inspection specified in AWL 53-61-153 of Bombardier TR 2B-2187, dated June 22, 2011; or Canadair Regional Jet TR 2B-2109, dated October 13, 2005; has been done as of January 16, 2013 (the effective date of AD 2012-25-02): The initial compliance time for AWL 53-61-153 is within 4,360 flight cycles after accomplishing the most recent special detailed inspection, or within 1,500 flight cycles after accomplishing the most recent detailed inspection as specified in AWL 53-61-153 of Canadair Regional Jet TR 2B-2109, dated October 13, 2005, whichever occurs later.
This paragraph restates the requirements of paragraph (j) of AD 2012-25-02, with a new exception. Except as required by paragraphs (j)(3), (l)(2), and (m) of this AD, after accomplishing the revisions required by paragraph (g) of this AD, no alternative actions (e.g., inspections) or intervals may be used other than those specified in Bombardier TR 2B-2187, dated June 22, 2011, to Appendix B-Airworthiness Limitations, of Part 2 of the Bombardier CL-600-2B19 MRM, unless the actions and intervals are approved as an alternative method of compliance (AMOC) in accordance with the procedures specified in paragraph (q)(1) of this AD.
This paragraph restates the requirements of paragraph (k) of AD 2012-25-02, with no changes. The maintenance program revision required by paragraph (g) of this AD may be done by inserting a copy of Bombardier TR 2B-2187, dated June 22, 2011, into Appendix B-Airworthiness Limitations, of Part 2 of the Bombardier CL-600-2B19 MRM. When this TR has been included in general revisions of the MRM, the general revisions may be inserted in the MRM, provided the relevant information in the general revision is identical to that in this TR.
Accomplish the actions required by paragraphs (j)(1), (j)(2), and (j)(3) of this AD at the time specified, except as provided by paragraphs (l) and (m) of this AD.
(1) At the applicable time specified in figure 1 to paragraph (j) of this AD: Do a nondestructive inspection for cracking of the forward face of the fuselage station (FS) 621 pressure bulkhead, in accordance with AWL 53-61-153 of Bombardier TR 2B-2187, dated June 22, 2011, to Appendix B—Airworthiness Limitations, of Part 2 of the Bombardier CL-600-2B19 MRM.
(2) At the applicable time specified in figure 1 to paragraph (j) of this AD: Modify the RPB and do a nondestructive inspection for cracking of the FS 621 pressure bulkhead web, in accordance with Bombardier Repair Engineering Order (REO) 601R-53-61-1240, Revision D, dated October 31, 2016.
(3) Before further flight after accomplishing the modification required by paragraph (j)(2) of this AD: Revise the existing maintenance or inspection program, as applicable, by incorporating the inspection requirements at the threshold and repetitive inspection times specified in the in-service deviation inspection requirements (SDIR) of Bombardier REO 601R-53-61-1240, Revision D, dated October 31, 2016.
(1) If any crack is found during any inspection required by paragraph (j)(2), (l)(1), or (m) of this AD: Before further flight, repair using a method approved by the Manager, New York ACO Branch, FAA; Transport Canada Civil Aviation (TCCA); or Bombardier, Inc.'s TCCA Design Approval Organization (DAO). If approved by the DAO, the approval must include the DAO-authorized signature.
(2) If any crack is found during any inspection required by paragraph (j)(1) of this AD: Before further flight, repair in accordance with the applicable service information specified in paragraph (k)(2)(i) or (k)(2)(ii) of this AD, or using a method approved by the Manager, New York ACO Branch, FAA; TCCA; or Bombardier, Inc.'s TCCA DAO. If approved by the DAO, the approval must include the DAO-authorized signature.
(i) Bombardier REO 601R-53-61-1230, Revision F, dated October 31, 2011; or Bombardier REO 601R-53-61-1285, Revision E, dated October 31, 2016.
(ii) Bombardier REO 601R-53-61-1240, Revision D, dated October 31, 2016; or Bombardier REO 601R-53-61-1541, Revision F, dated November 12, 2014.
For airplanes on which the actions required by paragraphs (j)(1) and (j)(2) of this AD were performed before the effective date of this AD using the REOs identified in figure 2 to paragraph (l) of this AD: In lieu of accomplishing the actions required by paragraph (j) of this AD, accomplish the actions required by paragraphs (l)(1) and (l)(2) of this AD within 6,000 flight cycles after the effective date of this AD.
(1) Perform a special detailed inspection for cracking of Zone B of the RPB web, in accordance with Part B of Bombardier REO 601R-53-61-1240, Revision D, dated October 31, 2016.
(2) Revise the existing maintenance or inspection program, as applicable, by incorporating the inspection requirements at the threshold and repetitive inspection times specified in Part B of the SDIR of Bombardier REO 601R-53-61-1240, Revision D, dated October 31, 2016. The inspection threshold is measured from the time of incorporation of the applicable REO specified in figure 2 to paragraph (l) of this AD.
For airplane serial number 7610: In lieu of accomplishing the actions required by paragraph (j) of this AD; within 6,000 flight cycles after the effective date of this AD, do a reinforcement of K601R36010—A at left buttock line (LBL) 27.5 and perform a special detailed inspection for cracking of the FS 621 pressure bulkhead web at LBL 27.5, in accordance with Bombardier REO 601R-53-61-5828, Revision A, dated March 16, 2017. Before further flight after accomplishing the reinforcement, or within 60 days after the effective date of this AD, whichever occurs later: Revise the maintenance or inspection program, as applicable, by incorporating the inspection requirements that include threshold and repetitive inspection times as specified in the SDIR of Bombardier REO 601R-53-61-5828, Revision A, dated March 16, 2017.
After the maintenance or inspection program has been revised as required by paragraph (j)(3), (l)(2), or (m) of this AD, no alternative actions (e.g., inspections) or intervals may be used unless the actions or intervals are approved as an AMOC in accordance with the procedures specified in paragraph (p)(1) of this AD.
(1) Accomplishment of the actions required by paragraph (j) or (l) of this AD terminates the requirements of paragraph (g) of this AD, for the repaired area only.
(2) Accomplishment of the actions required by paragraph (m) of this AD terminates the requirements of paragraph (g) of this AD.
(3) For airplanes on which the actions required by paragraph (j) or (l) of this AD have been done and on which the modification and inspection specified in REO 601R-53-61-1230, Revision F, dated October 31, 2011, have been done and there were no inspection findings: The actions required by paragraph (g) of this AD are terminated.
