AD 2008-08-21 Airworthiness Directives; Empresa Brasileira de Aeronautica S.A. (EMBRAER) Model ERJ 170 Airplanes and Model ERJ 190 Airplanes

Models named: ERJ 170-100 LR, -100 SE, -100 STD, -100 SU, -200 LR, -200 STD, -200 SU, ERJ 190-100 IGW, -100 LR, -200 IGW. Read the applicability below — it usually turns on serial or part numbers too.

This AD applies to all EMBRAER Model ERJ 170-100 LR, -100 SE, -100 STD, -100 SU, -200 LR, -200 STD, and -200 SU airplanes; and Model ERJ 190-100 IGW, -100 LR, -100 STD, -200 IGW, -200 LR, and -200 STD airplanes; certificated in any category.

You are responsible for having the actions required by this AD performed within the compliance times specified, unless the actions have already been done. Restatement of Requirements of AD 2006-11-15 Airplane Flight Manual (AFM) Revision (f) For Model ERJ 170-100 LR, -100 SE, -100 STD, and -100 SU airplanes; and Model ERJ 190-100 IGW, -100 LR, -100 STD airplanes: Within 7 days after June 14, 2006 (the effective date of AD 2006-11-15), revise the Limitations section of the EMBRAER 170/190 AFM to include the following statement. This may be done by inserting a copy of this AD in the AFM. Factory-installation or installation of the applicable software required by paragraph (h) of this AD terminates the AFM revision required by this paragraph. “After applying thrust reverser, do not move the throttle back to the forward thrust range, unless the REV icon on the EICAS is shown in amber or green.” Note 1: When a statement identical to that in paragraph (f) of this AD has been included in the general revisions of the AFM, the general revisions may be inserted into the AFM, and the copy of this AD may be removed from the AFM. New Requirements of This AD AFM Revision for New Airplanes (g) For Model ERJ 170-200 LR, -200 STD, and -200 SU airplanes; and Model ERJ 190-200 IGW, -200 LR, and -200 STD airplanes: Within 14 days after the effective date of this AD, revise the Limitations section of the EMBRAER 170/190 AFM to include the following statement. This may be done by inserting a copy of this AD in the AFM. Factory-installation or installation of the applicable software required by paragraph (h) of this AD terminates the AFM revision required by this paragraph. “After applying thrust reverser, do not move the throttle back to the forward thrust range, unless the REV icon on the EICAS is shown in amber or green.” Note 2: When a statement identical to that in paragraph (g) of this AD has been included in the general revisions of the AFM, the general revisions may be inserted into the AFM, and the copy of this AD may be removed from the AFM. Software Installation (h) Within 1,200 flight hours after the effective date of this AD, install the full-authority digital engine-control (FADEC) software specified in paragraph (h)(1), (h)(2), or (h)(3) of this AD, as applicable. Installing the applicable software terminates the applicable AFM revision required by paragraph (f) or (g) of this AD. (1) For Model ERJ 170-100 LR, -100 SE, -100 STD, -100 SU, -200 LR, -200 STD, and -200 SU airplanes identified in EMBRAER Service Bulletin 170-73-0003, Revision 01, dated September 4, 2006: Install engine FADEC software version 5.30 or higher in accordance with the service bulletin. (2) For the Model ERJ 190-200 LR airplane identified in EMBRAER Service Bulletin 190-73-0005, dated November 9, 2006: Install engine FADEC software version 5.10 or higher in accordance with the service bulletin. (3) For Model ERJ 190-100 IGW, -100 LR, -100 STD, -200 IGW, -200 LR, and -200 STD airplanes identified in EMBRAER Service Bulletin 190-73-0009, Revision 01, dated April 23, 2007: Install engine FADEC software version 5.20 or higher in accordance with the service bulletin. Alternative Methods of Compliance (AMOCs) (i)(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. Related Information (j) Brazilian airworthiness directive 2006-03-02R1, effective February 27, 2007; and Brazilian airworthiness directive 2006-03-03R1, effective November 9, 2007; also address the subject of this AD. Material Incorporated by Reference (k) You must use the service information listed in Table 1 of this AD to perform the actions that are required by this AD, as applicable, unless the AD specifies otherwise. The Director of the Federal Register approved the incorporation by reference of these documents in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. Contact Empresa Brasileira de Aeronautica S.A. (EMBRAER), P.O. Box 343-CEP 12.225, Sao Jose dos Campos-SP, Brazil, for a copy of this service information. You may review copies 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/cfr/ibr-locations.html . Table 1.—Material Incorporated by Reference EMBRAER Service Bulletin Revision level Date 170-73-0003 01 September 4, 2006. 190-73-0005 Original November 9, 2006. 190-73-0009 01 April 23, 2007. Issued in Renton, Washington, on April 8, 2008. Ali Bahrami, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. E8-8255 Filed 4-18-08; 8:45 am] BILLING CODE 4910-13-P

This AD results from a report that, during landing, the thrust reverser may not re-stow completely if the throttle lever is moved into the forward thrust range immediately after the thrust reverser is applied. We are issuing this AD to prevent the flightcrew from performing a takeoff with a partially deployed thrust reverser, which could result in reduced controllability of the airplane.