AD 2001-02-51 Airworthiness Directives; Empresa Brasileira de Aeronautica S.A. (EMBRAER) Model EMB-145 and EMB-135 Series Airplanes

Models named: EMB-145, EMB-135 series. Read the applicability below — it usually turns on serial or part numbers too.

Model EMB-145 and EMB-135 series airplanes, certificated in any category; having any serial number listed below: 145004 through 145103 inclusive 145105 through 145121 inclusive 145123 through 145139 inclusive 145141 through 145153 inclusive 145155 through 145189 inclusive 145191 through 145256 inclusive 145258 through 145262 inclusive 145264 through 145349 inclusive 145351 through 145362 inclusive 145364 145366 through 145369 inclusive

Required as indicated, unless accomplished previously. To prevent high pitch control forces, which could result in possible loss of control of the airplane, accomplish the following: AFM Revision        (a) Within 3 days after the effective date of this AD, revise the FAA-approved Airplane Flight Manual (AFM), as specified by paragraphs (a)(1), (a)(2), (a)(3), and (a)(4) of this AD. This may be accomplished by inserting a copy of this AD into the AFM.  (1) Revise the Limitations Section of the AFM, under “FLIGHT CONTROLS,” to include the following. “PITCH TRIM Maximum Airspeed after Takeoff/During Climb without Retrimming 160 KIAS”  (2) Revise the Emergency Procedures Section of the AFM, under “PITCH TRIM INOPERATIVE,” to delete the current information and replace it with the following: “PITCH TRIM INOPERATIVE EICAS WARNING: PIT TRIM 1(2) INOP (may be presented) EICAS CAUTION: AUTO TRIM FAIL (may be presented) If at least one Message is presented: Affected Pitch Trim System OFF Continue the flight with the remaining Pitch Trim System. If both Pitch Trim Systems are inoperative: Pitch Trim Main System OFF Pitch Trim Back Up System OFF Consider landing at the nearest suitable airport. If no Message is presented: Pitch Trim Command CHECK ALL SWITCHES If any Pitch Trim command is reestablished: Continue the flight with the remaining Pitch Trim System. NOTE: When Main Pitch Trim System is INOP, Autopilot is not available. WARNING: IF PITCH TRIM COMMAND IS NOT REESTABLISHED, DO NOT OPEN SPEEDBRAKE. If pitch trim command is not reestablished and the airplane presents a NOSE UP tendency: Airspeed REDUCE Airspeed reduction alleviates control column forces and may permit Pitch Trim command to be recovered. NOTE: Turning the airplane and extending the landing gear helps to maintain minimum airspeed with unwanted pitch up tendency. If it is necessary to reduce airspeed below 180 KIAS (or 200 KIAS in icing conditions), extend flaps to 9° (at 20,000 ft maximum). If it is necessary to reduce airspeed below 160 KIAS, extend flaps to 22° Pitch Trim Command CHECK ALL SWITCHES If pitch trim is recovered, retrim the airplane and proceed with flight normally. If pitch trim is not recovered: Consider landing at the nearest suitable airport. Approach and landing configuration: Landing Gear DOWN Flaps 22° Airspeed V REF 45 + 10 KIAS CAUTION: TO DETERMINE THE MINIMUM SUITABLE LANDING DISTANCE, MULTIPLY THE UNFACTORED LANDING DISTANCE FOR FLAPS 45° BY 1.27. If pitch trim command is not reestablished and the airplane presents a NOSE DOWN tendency: Airspeed REDUCE AS REQUIRED Below 250 KIAS: Flaps (at 20,000 ft maximum) 9° Below 200 KIAS: Flaps 22° Approach and landing configuration: Landing Gear DOWN NOTE: Gear extension should be delayed as long as possible. Flaps 22° Airspeed V REF 45 + 25 KIAS CAUTION: TO DETERMINE THE MINIMUM SUITABLE LANDING DISTANCE, MULTIPLY THE UNFACTORED LANDING DISTANCE FOR FLAPS 45° BY 1.44.  (3) Revise the Normal Procedures Section of the AFM, under the “BEFORE START” checklist, to delete the current information and insert the following: “Trims CKD/SET Actuate the pilot and copilot's Pitch Trim Switches and the backup pitch trim switch nose up and then nose down, and check correct indication on the EICAS. Hold trim input to verify that the trim motion stops after approximately 3 seconds. Set the pitch trim to the units required for takeoff. Set the roll and yaw trims to zero.               PITCH TRIM UNITS 8 7 6 5 4” CG POSITION (%) LESS THAN 25 30 35 40 43        (4) In the Normal Procedures Section of the AFM, under the “AFTER TAKEOFF” checklist, add the following: “Pitch Trim AS REQUIRED Keep the airplane trimmed to avoid excessive loads on the Horizontal Stabilizer Actuator (HSA). The airplane should be trimmed before 160 KIAS.”   Note 1: Incorporation of EMB145 AFM 145/1153, Revision 43, dated January 11, 2001, is also acceptable for compliance with the requirements of paragraph (a) of this AD. Placard Installation (b) Within 3 days after the effective date of this AD, install placards P/N 145-46718-001 at two positions on the main control panel within the pilot's primary field of view. Note 2: Installation per EMBRAER Alert Service Bulletin 145-27-A077, dated January 8, 2001, is also acceptable for compliance with the requirements of paragraph (b) of this AD. Alternative Methods of Compliance (c) An alternative method of compliance or adjustment of the compliance time that provides an acceptable level of safety may be used if approved by the Manager, Atlanta Aircraft Certification Office (ACO), FAA. Operators shall submit their requests through an appropriate FAA Principal Operations Inspector, who may add comments and then send it to the Manager, Atlanta ACO. Note 3: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Atlanta ACO. Special Flight Permits (d) Special flight permits may be issued in accordance with sections 21.197 and 21.199 of the Federal Aviation Regulations (14 CFR 21.197 and 21.199) to operate the airplane to a location where the requirements of this AD can be accomplished. Note 4: The subject of this AD is addressed in Brazilian emergency airworthiness directive 2001-01-01, dated January 18, 2001. Effective Date (e) This amendment becomes effective on February 7, 2001, to all persons except those persons to whom it was made immediately effective by emergency AD 2001-02-51, issued January 19, 2001, which contained the requirements of this amendment. Issued in Renton, Washington, on January 26, 2001. Donald L. Riggin, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 01-2742 Filed 2-1-01; 8:45 am] BILLING CODE 4910-13-U