Airworthiness Directive · Amendment 39-11718 · EMBRAER Model EMB-145 Series Airplanes
EMBRAER Model EMB-145 Series Airplanes
Model EMB-145 series airplanes, serial numbers 145004 through 145047 inclusive and 145049 through 145051 inclusive; certificated in any category; equipped with IC-600 #1 having part number (P/N) 7017000-82402; excluding those airplanes on which the modification specified in any of the following EMBRAER service bulletins has been accomplished: EMBRAER Service Bulletin S.B. 145-22-0001, dated May 7, 1998; EMBRAER Service Bulletin S.B. 145-22-0004, Revision 01, dated July 30, 1998; EMBRAER Service Bulletin S.B. 145-31-0007, Revision 02, dated June 30, 1998.
Note 1: This AD applies to each airplane identified in the preceding applicability provision, regardless of whether it has been otherwise 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 (c) 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 supersedes an existing airworthiness directive (AD), applicable to certain EMBRAER Model EMB-145 series airplanes, that currently requires revisions to the Airplane Flight Manual (AFM) to provide the flight crew with updated procedures for prohibiting use of the autopilot below 1,500 feet above ground level, emergency procedures for pitch trim runaway, and abnormal procedures for autopilot trim failure and stabilizer out of trim. That AD also requires installation of certain warning placards. This amendment requires replacement of a certain integrated computer with a new integrated computer; installation of an upgraded integrated computers checklist; and removal of certain placards and certain limitations in the AFM. 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 failure of the pitch trim system, which could cause undetected autopilot trim runaway, and consequent reduced controllability of the airplane, uncommanded autopilot disconnect, and excessive altitude loss.
To prevent failure of the pitch trim system, which could cause undetected autopilot trim runaway, and result in reduced controllability of the airplane, uncommanded autopilot disconnect, and excessive altitude loss; accomplish the following:
(a) Within 20 flight hours after February 2, 1999 (the effective date of AD 99-01-12, amendment 39-11015), accomplish paragraphs (a)(1), (a)(2), (a)(3), and (a)(4) of this AD.
(1) Install warning placards, P/N 145-39641-001, on the left and right sides of the cockpit glare shield panel, using double-face tape (or similar), in accordance with EMBRAER Alert Service Bulletin S.B. 145-31-A010, dated December 15, 1998, which states:
“DO NOT OPERATE AUTOPILOT BELOW 1,500 FT A.G.L.”
(2) Revise the Limitations Section of the FAA-approved Airplane Flight Manual (AFM) (in the “AUTOPILOT” section) to include the information contained in this paragraph of the AD. This may be accomplished by inserting a copy of this AD in the AFM.
THE USE OF AUTOPILOT BELOW 1,500 FEET IS PROHIBITED.”
(3) Revise the Emergency Procedures Section of the FAA-approved AFM (in the “PITCH TRIM RUNAWAY” section) to include the following statement. This may be accomplished by inserting a copy of this AD in the AFM.
Immediately and simultaneously:
Control Column—HOLD FIRMLY
Quick Disconnect Button—PRESS AND HOLD
Pitch Trim Main System—OFF
Pitch Trim Back Up System—OFF
Quick Disconnect Button—RELEASE
If control column forces are excessive, try to recover airplane control by turning one system on and trimming the airplane as necessary. Initiate with the backup system. Leave the failed system off.
If neither system is operative:
PITCH TRIM INOPERATIVE Procedure—COMPLETE
Autopilot—OFF
Do not use the autopilot for the remainder of the flight.”
(4) Revise the Abnormal Procedures Section of the FAA-approved AFM (in the “AUTOPILOT” section) to include the following statement. This may be accomplished by inserting a copy of this AD in the AFM.
PITCH TRIM RUNAWAY Procedure—PERFORM
PITCH TRIM RUNAWAY Procedure—PERFORM”
(b) Within 500 flight hours after the effective date of this AD, accomplish paragraphs (b)(1) and (b)(2) of this AD. Accomplishment of paragraph (b) of this AD constitutes terminating action for the requirements of paragraph (a) of this AD.
(1) Replace the integrated computer IC-600 #1, P/N 7017000-82402, with a new integrated computer, P/N 7017000-82422; install an upgraded integrated computers checklist; and remove warning placards, P/N 145-39641-001, on the left and right sides of the cockpit glare shield panel required by paragraph (a)(1) of this AD; in accordance with EMBRAER Service Bulletin S.B. 145-31-0010, dated March 18, 1999.
Note 2: Installation of an upgraded integrated computers checklist is required only if an integrated computers checklist is currently installed on the airplane.
(2) Remove the limitations required by paragraphs (a)(2), (a)(3), and (a)(4) of this AD from the AFM.
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.
Aircraft
