AD 2006-12-21

You are responsible for having the actions required by this AD performed within the compliance times specified, unless the actions have already been done.

Note 1: Bombardier Service Letter RJ-SL-27-002A, dated April 8, 1998, and Service Letter RJ-SL-27-037, dated July 2, 1998, may provide operators with additional information concerning the actions required by this AD. However, accomplishment of the procedures specified in these service letters should not be considered to be an acceptable method of compliance with the requirements of this AD.

(f) Within 10 days after October 2, 1998 (the effective date of AD 98-20-01), accomplish the requirements of paragraphs (f)(1), (f)(2), and (f)(3) of this AD.

(1) Revise the Limitations Section of the FAA-approved airplane flight manual (AFM) to include the following procedures and Figures 1 and 2 of this AD. After accomplishing the actions in paragraphs (h) and (i) of this AD, remove the revisions required by this paragraph of this AD from the AFM.

“Air Operator Actions

Important: If the outboard flap position is outside the “GO” range, as shown in figure 2., further flight is prohibited until required maintenance actions have been accomplished.

1. Touch-and-go landings for the purposes of training must be accomplished using a flap setting of 20 degrees for the entire procedure.

2. (a) Take-off flaps must be set prior to departure, and

(b) An external visual check must be accomplished to detect any twisting, skewing, or abnormal deformation of the flaps, using the information given in Figures 1 and 2.

Note 1: If the outboard flap position is outside the “GO” range as shown in figure 2., further flight is prohibited until required maintenance actions have been accomplished.

Note 2: This visual check must be accomplished either by a member of the flight crew or by maintenance personnel, and the results reported directly to the pilot-in-command prior to take-off.

3. If any additional change to the flap position is necessary, prior to take-off, accomplish the visual check specified by the preceding paragraph 2. (b).”

(2) Revise the Normal Procedures Section of the FAA-approved AFM to include the following procedures:

“To minimize a possible flap twist in flight when operating flaps, operate the flap selector sequentially, stopping at each setting (i.e., 0 degrees, 8 degrees if applicable, 20 degrees, 30 degrees, 45 degrees; or operate the flap selector in reverse order), and waiting for the flaps to reach each position before selecting the next setting. Monitor the control wheel for abnormal control wheel angles during each transition in flap position.

Note: This procedure is not applicable during a go-around or during any emergency aircraft handling procedure where prompt flap retraction is required. In these cases, follow the applicable AFM procedures.”

(3) Revise the Abnormal Procedures Section of the FAA-approved AFM to include the following procedures.

“If abnormal aileron control wheel angles develop during flap operation with the autopilot on, or if the aircraft rolls without pilot input with the autopilot off (with or without a ‘FLAPS FAIL’ caution message), perform the following actions:

1. If flaps are being extended, immediately return the flaps to the previously selected position (e.g., for flaps selected from 8 degrees to 20 degrees, re-select 8 degrees).

2. If flaps are being retracted, the flap selector should remain in the currently selected position (e.g., for flaps selected from 20 degrees to 8 degrees, leave selector at 8 degrees).

3. Do not attempt to operate the flaps any further.

4. If the flaps are engaged, disconnect the autopilot.

Note: When disconnecting the autopilot, anticipate an out-of-trim situation and hold the aileron control wheel in its current position.

5. For landing, perform the “Flaps Failure” procedure for the following conditions:

(a) If an abnormal aileron control wheel angle to the left develops, do not land if a crosswind from the left is greater than 20 knots.

(b) If an abnormal aileron control wheel angle to the right develops, do not land if a crosswind from the right is greater than 20 knots.

6. After landing, do not attempt to retract the flaps. Record the event in the Aircraft Maintenance Log Book and notify the person responsible for maintenance.”

(g) Within 10 days after October 2, 1998, revise the FAA-approved maintenance program to include the following procedures and Figures 1 and 2 of this AD:

“Maintenance Procedure

Whenever a “FLAPS FAIL” caution message occurs, carry out the following procedures after landing:

Note: These procedures are to be accomplished by maintenance personnel only.

1. Check that there have been no other “FLAPS FAIL” caution messages reported within the previous 72 hours. If a previous message has been reported, prior to further flight, perform the actions required in the following Maintenance Action section. If no previous “FLAPS FAIL” caution message has been reported, continue with the following:

2. Carry out an external visual check of each outboard flap for evidence of twisting, skewing, or abnormal deformation. (Reference Figures 1 and 2.)

3. If there is no evidence of twisting, skewing, or abnormal deformation, proceed as follows:

(a) Reset the flap system ONLY ONCE by cycling circuit breakers CB1-F4 and CB2-F4.

(b) If the system does not reset (i.e., the “FLAPS FAIL” caution message is still posted), prior to further flight, perform the actions required in the following Maintenance Action section.

(c) If the system resets, cycle the flaps to 45 degrees and back to 0 degrees. Continued flap operation for up to a maximum of 72 hours is then permitted as long as no additional “FLAPS FAIL” caution message is indicated.

(d) If an additional “FLAPS FAIL” caution message occurs within the period of 72 hours, as specified above, prior to further flight, perform the actions required in the following Maintenance Action section.

(e) Within 72 hours, even if no further “FLAPS FAIL” messages have been indicated, perform the actions required in the following Maintenance Action section.

4. If there is evidence of twisting, skewing, or abnormal deformation, PRIOR TO FURTHER FLIGHT, perform the actions required in the following Maintenance Action section.

Maintenance Action

Whenever the outboard flap position indicator is outside the “GO” range as shown in Figure 2, or whenever directed to do so by the Maintenance Procedure above, perform the following procedures:

A. Interrogate the flap electronic control unit (FECU) per Fault Isolation Manual, Section 27-50-00, “Flaps Fault Isolation,” and rectify as applicable.

B. Visually check each flap for evidence of twisting, skewing, or abnormal deformation.

1. If there is no evidence of twisting, skewing, or abnormal deformation, manually isolate any jammed, disconnected, or dragging component; and rectify all discrepant conditions.

2. If there is evidence of twisting, skewing, or abnormal deformation, replace both actuators and any discrepant flap panel with new or serviceable components. In addition, inspect flexible shaft(s) inboard of the most outboard actuator removed for discrepancies, and replace any discrepant flexible shaft with a new or serviceable flexible shaft.

Note: An acceptable procedure for testing the flap drive breakaway input torque is detailed in Aircraft Maintenance Manual Temporary Revision 27-203, Task 27-53-00-750-802, dated July 17, 1998.

C. Within 3 days after identifying a flap panel twist or logging a “FLAPS FAIL” caution message, notify Bombardier Aerospace, via the Canadair Regional Jet Action Center, of all findings and actions taken.”

Within 12 months after the effective date of this AD: Install new Number 3 and Number 4 flap actuators in accordance with the Accomplishment Instructions of Bombardier Service Bulletin 601R-27-114, excluding Appendix A, Revision C, dated November 9, 2004. The actions in paragraph (h) of this AD must be accomplished prior to or concurrently with the actions in paragraph (i) of this AD.

(i) Within 30 months after the effective date of this AD, but after the actions required by paragraph (h) of this AD have been accomplished: Install the SDS in accordance with paragraphs (i)(1), (i)(2), (i)(3), (i)(4), and (i)(5) of this AD. These actions must be accomplished in the order stated in this paragraph. Accomplishing the actions in paragraphs (h) and (i) of this AD terminates the requirements of paragraphs (f) and (g) (the requirements of AD 98-20-01) of this AD, and the AFM revisions required by those paragraphs may be removed from the AFM.

(1) Install the electrical provisions for the SDS in accordance with the Accomplishment Instructions of Bombardier Service Bulletin 601R-27-115, Revision E, dated October 7, 2004. Although the service bulletin specifies to submit certain information to the manufacturer, this AD does not include that requirement.

(2) Install and activate the SDS in accordance with the Accomplishment Instructions of Bombardier Service Bulletin 601R-27-116, Revision C, dated August 26, 2004; and install a new or retrofitted air data computer (ADC) in accordance with the Accomplishment Instructions of Bombardier Service Bulletin 601R-34-128, Revision C, dated March 28, 2005. Although the service bulletin specifies to submit certain information to the manufacturer, this AD does not include that requirement.

(3) Install new airspeed limitation placards in accordance with the Accomplishment Instructions of Bombardier Service Bulletin 601R-11-080, Revision A, dated October 11, 2005.

(4) Revise the Limitations section of the AFM to include the information specified in Canadair Temporary Revision (TR) RJ/128, dated November 28, 2003, to Canadair Regional Jet AFM, CSP A-012, to include revised V FE values, and a new SDS and crosswind-related limitation for take-off flap selection.

Note 2: The action in paragraph (i)(4) of this AD may be accomplished by inserting a copy of Canadair TR RJ/128 in the AFM. When this temporary revision has been incorporated into the general revisions of the AFM, the general revisions may be inserted in the AFM, provided the information contained in the general revision is identical to that specified in Canadair TR RJ/128.

(5) For airplanes on which decals stating “Visually inspect flaps prior to departure” have been installed in production or in accordance with an alternative method of compliance (AMOC) granted by the FAA: After the installation required by paragraphs (h)(1), (i)(1), (i)(2), (i)(3), and (i)(4) of this AD, remove the decals in accordance with Part A of Bombardier Service Bulletin 601R-27-111, dated March 6, 2000. Although the service bulletin specifies to submit certain information to the manufacturer, this AD does not include that requirement.

Actions accomplished before the effective date of this AD according to the service bulletins identified in paragraphs (j)(1), (j)(2), (j)(3), and (j)(4) of this AD, are considered acceptable for compliance with the corresponding action specified in paragraphs (h) and (i) of this AD.

(1) For the action in paragraph (h) of this AD: Bombardier Service Bulletin 601R-27-114, dated March 22, 2002; Revision A, dated November 6, 2002; or Revision B, dated December 4, 2003.

(2) For the actions in paragraph (i)(1) of this AD: Bombardier Service Bulletin 601R-27-115, Revision D, dated March 18, 2004.

(3) For the actions in paragraph (i)(2) of this AD: Bombardier Service Bulletin 601R-27-116, dated July 23, 2003; Revision A, dated September 10, 2003; or Revision B, dated February 2, 2004; and Bombardier Service Bulletin 601R-34-128, Revision B, dated September 7, 2001.

(4) For the actions in paragraph (i)(3) of this AD: Bombardier Service Bulletin 601R-11-080, dated November 28, 2003.

(k)(1) As of 12 months after the effective date of this AD, no person may install on any airplane a flap actuator with part numbers (P/Ns) 601R93103-5, -6, -7, -8, -9, -10, -11, -12, -17, and -18 (Vendor P/Ns 853D100-7, -8, -9, -10, -11, -12, -13, -14, -17 and -18).

(2) As of 12 months after the effective date of this AD, no person may install on any airplane a flap actuator with P/Ns 601R93104-5, -6, -7, -8, -9 and -10 (Vendor P/Ns 854D100-7, -8, -9, -10, -11 and -12).

(3) As of 30 months after the effective date of this AD, no person may install on any airplane an ADC with P/Ns 822-0372-140 and -143.