Airworthiness Directive · Amendment 39-13814 · Bombardier Model CL-600-2B19 (Regional Jet Series 100 & 440) Airplanes
Bombardier Model CL-600-2B19 (Regional Jet Series 100 & 440) Airplanes
Superseded. A later AD replaced this one: AD 2007-01-07. Comply with the one in force.
This AD applies to Bombardier Model CL-600-2B19 (Regional Jet Series 100 & 440) airplanes, serial numbers 7003 through 7067 inclusive and 7069 through 8999 inclusive, certificated in any category; equipped with main landing gear (MLG) main fittings, part number (P/N) 601R85001-3 or -4 (Messier Dowty P/N 17064-101, -102, -103, or -104).
The FAA is adopting a new airworthiness directive (AD) for certain Bombardier Model CL-600-2B19 (Regional Jet Series 100 & 440) airplanes. This AD 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 AD is prompted by 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.
The term “service bulletin,” as used in this AD, means the Accomplishment Instructions of Bombardier Alert Service Bulletin A601R-32-099, including Appendices A, B, and D, and excluding Appendix C, dated September 15, 2004.
Do the actions specified in Table 1 of this AD.
| Do— | At 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 service bulletin | (i) Before the accumulation of 8,000 total flight cycles since the main fitting of the MLG was new. (ii) Within 8,000 flight cycles since the last overhaul of the MLG. (iii) 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 service bulletin | (i) Before the accumulation of 8,000 total flight cycles since the main fitting of the MLG was new. (ii) Within 8,000 flight cycles since the last overhaul of the MLG. (iii) Within 500 flight cycles after the effective date of this AD. |
| (3) An ultrasonic inspection for cracks of the left and right main fittings of the MLG, in accordance with Part C of the service bulletin | (i) Before the accumulation of 8,000 total flight cycles since the main fitting of the MLG was new. (ii) Within 8,000 flight cycles since the last overhaul of the MLG. (iii) Within 500 flight cycles after the effective date of this AD. |
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 mirrors magnifying lenses, etc. may be necessary. Surface cleaning and elaborate procedures may be required.”
Repeat the inspections required by paragraph (g) of this AD at the time specified in Table 2 of this AD.
| For the inspection required by— | Repeat at intervals not to exceed— | Until the action required by— |
|---|---|---|
| (1) Paragraph (g)(1) of this AD | 5 days | Paragraph (g)(3) of the AD is done, unless required by paragraph (j) of this AD. |
| (2) Paragraph (g)(2) of this AD | 500 flight cycles | Paragraph (j)(2) of this AD is done. |
| (3) Paragraph (g)(3) of this AD | 5,000 flight cycles, 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)(1), or (j)(1) of this AD, before further flight, do the actions specified in paragraphs (i)(1) or (i)(2) of this AD in accordance with Part A of the service bulletin.
(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)(2) of this AD, do the actions specified in Table 3 of this AD in accordance with Part B of the service bulletin.
| 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 paragraph (g)(2) or (h)(2) of this AD, as aplicable | 5 days | Paragraph (j)(2) 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)(2) of this AD, as applicable | 500 flight cycles | (None). |
(k) If there is an indication of a crack during any inspection required by paragraph (g)(3), (h)(3), or (j)(2) 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 service bulletin.
Although the service bulletin referenced in this AD specifies to submit certain information to the airplane manufacturer and to return cracked main fittings to the supplier, this AD does not include those requirements.
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.
