Airworthiness Directive · Amendment 39-14879 · Bombardier Model CL-600-2B19 (Regional Jet Series 100 & 440) Airplanes
Bombardier Model CL-600-2B19 (Regional Jet Series 100 & 440) Airplanes
This AD applies to Bombardier Model CL-600-2B19 (Regional Jet Series 100 & 440) airplanes, certificated in any category; serial numbers 7003 through 7067 inclusive, and 7069 through 8999 inclusive; equipped with main landing gear (MLG) main fittings, having part number (P/N) 601R85001-3 or -4 (Messier-Dowty P/N 17064-101, -102, -103, or -104).
The FAA is superseding an existing airworthiness directive (AD), that applies to certain Bombardier Model CL-600-2B19 (Regional Jet Series 100 & 440) airplanes. That AD currently requires repetitive inspections for cracks, sealant damage, and corrosion of the main fittings of the main landing gear (MLG), and corrective actions if necessary. This new AD reduces the compliance times for inspecting certain low-utilization airplanes, and provides a terminating action for the repetitive inspections. This AD results from a report of a cracked main fitting of the MLG. We are issuing this AD to detect and correct fatigue cracking of the main fitting of the MLG and consequent failure of the main fitting, which could result in the collapse of the MLG.
You are responsible for having the actions required by this AD performed within the compliance times specified, unless the actions have already been done.
Unless otherwise specified in this AD, the term “service bulletin,” as used in this AD, means the Accomplishment Instructions of the applicable service bulletin identified in paragraph (f)(1) or (f)(2) of this AD.
(1) For the actions specified in paragraphs (g), (h), (i), (j), and (k) of this AD: Bombardier Alert Service Bulletin A601R-32-099, including Appendices A, B, and D, and excluding Appendix C, dated September 15, 2004; or Bombardier Alert Service Bulletin A601R-32-099, Revision A, including Appendices A, B, and D, and excluding Appendix C, dated December 13, 2004; or Bombardier Alert Service Bulletin A601R-32-099, Revision B, dated June 16, 2005, including Appendices A, B, and D, and excluding Appendix C, Revision A, dated December 13, 2004.
(2) For the actions specified in paragraph (l) of this AD: Bombardier Service Bulletin 601R-32-093, Revision B, dated July 14, 2005.
(3) After the effective date of this AD, only Revision B of Bombardier Alert Service Bulletin A601R-32-099, dated July 16, 2005, may be used for the actions specified in paragraphs (g), (h), (i), (j), and (k) of this AD.
(4) Although the service bulletins identified in paragraph (f)(1) of this AD specify to submit certain information to the airplane manufacturer and to return cracked main fittings to the supplier, this AD does not include those requirements.
Do the actions in Table 1 of this AD.
| At the earlier of the times specified in Column 2 or Column 3— | Column 2—The latest of— | Column 3—The latest of— |
|---|---|---|
| (1) A detailed inspection for cracks of the inboard and outboard sides of the main fitting of the MLG between the pintle pin trunnion and the radius of the shock strut lug, in accordance with Part A of the applicable service bulletin | (i)(A) Before the accumulation of 8,000 total flight cycles since the main fitting of the MLG was new. (B) Within 8,000 flight cycles since the last overhaul of the MLG done before the effective date of this AD. (C) Within 50 flight cycles after October 21, 2004 (the effective date of AD 2004-20-09). | (ii)(A) Within 48 months since the main fitting of the MLG was new. (B) Within 48 months since the last overhaul of the MLG done before the effective date of this AD. (C) Within 50 flight cycles after the effective date of this AD. |
| (2) A detailed inspection for sealant damage or corrosion around the forward bushing of the left and right main fittings of the MLG, in accordance with Part B of the applicable service bulletin | (i)(A) Before the accumulation of 8,000 total flight cycles since the main fitting of the MLG was new. (B) Within 8,000 flight cycles since the last overhaul of the MLG done before the effective date of this AD. (C) Within 500 flight cycles after October 21, 2004. | (ii)(A) Within 48 months since the main fitting of the MLG was new. (B) Within 48 months since the last overhaul of the MLG done before the effective date of this AD. (C) Within 500 flight cycles or 6 months after the effective date of this AD, whichever occurs first. |
| (3) An ultrasonic inspection for cracks of the left and right main fittings of the MLG, in accordance with Part C of the applicable service bulletin | (i)(A) Before the accumulation of 8,000 total flight cycles since the main fitting of the MLG was new. (B) Within 8,000 flight cycles, since the last overhaul of the MLG done before the effective date of this AD. (C) Within 500 flight cycles after October 21, 2004. | (ii)(A) Within 48 months since the main fitting of the MLG was new. (B) Within 48 months since the last overhaul of the MLG done before the effective date of this AD. (C) Within 500 flight cycles or 6 months after the effective date of this AD, whichever occurs first. |
Note 1: 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.”
Repeat the inspections in paragraph (g) of this AD thereafter at the applicable interval in paragraph (h)(1) or (h)(2) of this AD, until the terminating action required by paragraph (l) of this AD is accomplished.
(1) For airplanes on which the applicable initial inspection in paragraph (g) of this AD has been done before the effective date of this AD, do the next inspection at the applicable interval in Table 2 of this AD.
(2) For airplanes on which the applicable initial inspection in paragraph (g) of this AD has not been done before the effective date of this AD, repeat the inspection at the applicable interval in Table 2 of this AD.
| For the inspection required by— | Repeat at intervals not to exceed— | Until the action required by— |
|---|---|---|
| (3) Paragraph (g)(1) of this AD | 5 days | Paragraph (g)(3) of this AD is done, unless required by paragraph (j) of this AD. |
| (4) Paragraph (g)(2) of this AD | 500 flight cycles or 6 months, whichever occurs first | Paragraph (j)(2) of this AD is done. |
| (5) Paragraph (g)(3) of this AD | 5,000 flight cycles or 30 months, whichever occurs first, except as required by paragraph (j)(2) of this AD | (None). |
(i) If there is an indication of a crack during any inspection required by paragraph (g)(1), (h)(3), or (j)(1) of this AD, before further flight, do the actions specified in paragraph (i)(1) or (i)(2) of this AD in accordance with part A of the applicable service bulletin; or do the terminating action required by paragraph (l) of this AD before further flight.
(1) Replace the cracked main fitting of the MLG with a new or serviceable main fitting.
(2) Do an eddy current inspection to verify whether there is a crack. If there is a crack, replace the cracked main fitting of the MLG with a new or serviceable main fitting.
(j) If any sealant damage or corrosion is found during any inspection required by either paragraph (g)(2) or (h)(4) of this AD, do the actions specified in Table 3 of this AD in accordance with part B of the applicable service bulletin, until the terminating action required by paragraph (l) of this AD is accomplished.
| Do the inspection specified in— | Within— | Repeat at intervals not to exceed— | Until the action specified in— |
|---|---|---|---|
| (1) Paragraph (g)(1) of this AD | 5 days after doing the inspection required by (g)(2) or (h)(4) of this AD, as applicable | 5 days | Paragraph (j)(2) or (l) of this AD is done. |
| (2) Paragraph (g)(3) of this AD | 500 flight cycles after doing the inspection required by paragraph (g)(2) or (h)(4) of this AD, as applicable | 500 flight cycles | Paragraph (l) of this AD is done. |
(k) If there is an indication of a crack during any inspection required by paragraph (g)(3) or (h)(5) of this AD, before further flight, replace the cracked main fitting of the MLG with a new or serviceable main fitting in accordance with part C of the applicable service bulletin; or do the terminating action required by paragraph (l) of this AD before further flight.
Within 15 months after the effective date of this AD, replace both main fittings of the MLG with new main fittings having new part numbers, in accordance with the Accomplishment Instructions of Bombardier Service Bulletin 601R-32-093, Revision B, dated July 14, 2005. Doing this replacement terminates all requirements of paragraphs (g), (h), (i), (j), and (k) of this AD.
Note 2: Bombardier Service Bulletin 601R-32-093, Revision B, refers to Messier-Dowty Service Bulletin M-DT SB17002-32-24, dated October 9, 2003; and Messier-Dowty Service Bulletin M-DT SB17002-32-25, Revision 1, dated October 17, 2003; as additional sources of service information for replacing the MLG main fitting.
Actions done before the effective date of this AD in accordance with the service bulletins listed in Table 4 of this AD are acceptable for compliance with the corresponding action specified in this AD.
| Service Bulletin | Revision level | Date |
|---|---|---|
| Bombardier Service Bulletin 601R-32-093 | Original | October 17, 2003. |
| Bombardier Service Bulletin 601R-32-093 | A | September 21, 2004. |
As of the effective date of this AD, no person may install a main fitting of the MLG, Bombardier P/N 601R85001-3 or 601R85001-4; also referred to as Messier-Dowty P/N 17064-101, 17064-102, 17064-103, or 17064-104; on any airplane.
The aircraft, engines and makers this AD names, by the model designations in its text. A model listed here may still be outside the AD's serial ranges.
