AD 2008-15-01 Airworthiness Directives; Empresa Brasileira de Aeronautica S.A. (EMBRAER) Model EMB-120, -120ER, -120FC, -120QC, and -120RT Airplanes

Models named: EMB-120, -120ER, -120FC, -120QC, -120RT. Read the applicability below — it usually turns on serial or part numbers too.

All Model EMB-120, -120ER, -120FC, -120QC, and -120RT airplanes, certificated in any category.

Required as indicated, unless accomplished previously. To prevent pitch trim upsets if the pitch trim actuators jam or freeze, which could result in reduced controllability of the airplane, accomplish the following: Revision of Airplane Flight Manual (AFM): AFM-120/794 (a) Within 100 flight hours after the effective date of this AD, revise the FAA-approved AFM, EMBRAER AFM-120/794, as specified in paragraphs (a)(1) and (a)(2) of this AD. These actions may be accomplished by inserting a copy of this AD into the AFM. (1) Revise the FLIGHT CONTROLS FAILURES paragraph of the Abnormal Procedures section by replacing the existing ELEVATOR TRIM JAMMING procedure with the following: “ELEVATOR TRIM JAMMING       Control Wheel Hold Firmly Autopilot Disengage Airspeed Reduce Note: Minimum airspeed with flap 0°—160 KIAS       Pitch trim command Check all switches and elevator trim wheel If pitch trim is recovered: Re-trim the airplane and continue the flight with the autopilot disengaged, not exceeding the airspeed when the trim was recovered. If pitch trim is not recovered: Land at the nearest suitable airport. Approach and landing configuration:       Landing gear Down Flaps 25 Airspeed Vref25 CAUTION: DO NOT TRY TO RE-ENGAGE THE AUTOPILOT.” (2) Revise the Normal Procedures section of the AFM, after the current checklist item for activating the FASTEN BELTS switch, by inserting the following: “PITCH TRIM SYSTEM CHECK       Control Wheel Hold firmly Autopilot Disengage Power Levers As required Elevator Trim Wheels As required CAUTION: MANUALLY SET THE ELEVATOR TRIM WHEELS TO THE REQUIRED DESCENT ATTITUDE. If any trim system binding (if trim wheel rotates more than one trim wheel index mark after being released), or abnormal trim operation is observed:       Elevator Trim Jamming Procedure Perform CAUTION: DO NOT TRY TO RE-ENGAGE THE AUTOPILOT. If no abnormal trim operation is observed:       Flight Director Vertical Mode As required Autopilot Reengage” AFM Revision: Collins APS-65B Autopilot AFM Supplement (b) Concurrently with the AFM revisions required by paragraph (a) of this AD, revise the Limitations section of the Collins APS-65B Autopilot System Supplement to include the following (this may be accomplished by inserting a copy of this AD into the AFM Supplement): “1) The autopilot must not be used during descent unless a trim check has been performed successfully prior to descent, as follows: PITCH TRIM SYSTEM CHECK       Control Wheel Hold firmly Autopilot Disengage Power Levers As required Elevator Trim Wheels As required CAUTION: MANUALLY SET THE ELEVATOR TRIM WHEELS TO THE REQUIRED DESCENT ATTITUDE. If any trim system binding (if trim wheel rotates more than one trim wheel index mark after being released), or abnormal trim operation is observed:       Elevator Trim Jamming Procedure Perform CAUTION: DO NOT TRY TO RE-ENGAGE THE AUTOPILOT. If no abnormal trim operation is observed:       Flight Director Vertical Mode As required Autopilot Reengage 2) If an elevator trim jamming is detected during flight and the pitch trim system resumes normal operation on ground, only a ferry flight using a special permit may be performed to return the aircraft to a maintenance base for replacement of the actuators. In this case, the use of autopilot is prohibited.” Placard Installation (c) Within 300 flight hours after the effective date of this AD, install two placards on the glareshield, advising the flight crew to check the pitch trim before initial descent, in accordance with Part II of the Accomplishment Instructions of EMBRAER Service Bulletin 120-25-0262, Change 02, dated October 30, 2003. Elevator Trim System Modification (d) Within 36 months after the effective date of this AD, modify the elevator trim system, in accordance with the Accomplishment Instructions of EMBRAER Service Bulletin 120-27-0095, Revision 01, dated October 30, 2007; and EMBRAER Service Bulletin 120-27-0096, Revision 01, dated October 1, 2007. Accomplishment of the modification terminates the requirements of paragraphs (a), (b), and (c) of this AD, and the corresponding AFM revisions and placards may be removed. Credit for Prior Accomplishment (e) A modification done before the effective date of this AD in accordance with EMBRAER Service Bulletins 120-27-0095 and 120-27-0096, both dated February 16, 2007, is acceptable for compliance with the requirements of paragraph (d) of this AD. Parts Installation (f) As of 36 months after the effective date of this AD, no person may install, on any airplane, an elevator trim tab actuator or control cable having a part number identified in Table 1 of this AD. Table 1.—Prohibited Parts Part Part No. Elevator trim tab actuator 120-19685-001; 120-19685-003; 120-19685-007; 120-38650-001; 120-39205-001; 5299; 5299-1. Control cable 120-27729-095; 120-27729-097; 120-31370-095; 120-31370-097. Alternative Methods of Compliance (g)(1) The Manager, International Branch, ANM-116, Transport Airplane Directorate, FAA, has the authority to approve AMOCs for this AD, if requested in accordance with the procedures found in 14 CFR 39.19. (2) To request a different method of compliance or a different compliance time for this AD, follow the procedures in 14 CFR 39.19. Before using any approved AMOC on any airplane to which the AMOC applies, notify your appropriate principal inspector (PI) in the FAA Flight Standards District Office (FSDO), or lacking a PI, your local FSDO. Incorporation by Reference (h) You must use the service information contained in Table 2 of this AD to do the actions required by this AD, unless the AD specifies otherwise. (1) The Director of the Federal Register approved the incorporation by reference of this service information under 5 U.S.C. 552(a) and 1 CFR part 51. (2) For service information identified in this AD, contact Empresa Brasileira de Aeronautica S.A. (EMBRAER), P.O. Box 343—CEP 12.225, Sao Jose dos Campos—SP, Brazil. (3) You may review copies of the service information that is incorporated by reference at the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington; or at the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, call 202-741-6030, or go to http://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html. Table 2.—Material Incorporated by Reference Service Bulletin Revision level Date EMBRAER Service Bulletin 120-25-0262 Change 02 October 30, 2003. EMBRAER Service Bulletin 120-27-0095 Revision 01 October 30, 2007. EMBRAER Service Bulletin 120-27-0096 Revision 01 October 1, 2007. Note 1: The subject of this AD is addressed in Brazilian airworthiness directive 2001-06-01R4, effective August 23, 2007. Effective Date (i) This amendment becomes effective on August 21, 2008. Issued in Renton, Washington, on July 3, 2008. Ali Bahrami, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. E8-15969 Filed 7-16-08; 8:45 am] BILLING CODE 4910-13-P