AD 2008-05-02

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

Within 5 days after December 23, 2005 (the effective date of AD 2005-25-04): Review the airplane maintenance records to determine whether any vibration from the tail section or rudder pedals was reported within 120 flight hours or 100 flight cycles before December 23, 2005.

At the applicable time specified in paragraph (g)(1) or (g)(2) of this AD: Do a detailed inspection of the skin, attachment fittings, and control rods of rudder II to detect cracks, loose parts, wear, or damage. Inspect in accordance with the Accomplishment Instructions of EMBRAER Alert Service Bulletin 145LEG-55-A010, dated August 26, 2005 (for Model EMB-135BJ airplanes); or 145-55-A036, Revision 01, dated September 5, 2005 (for all other airplanes); except as provided by paragraph (l) of this AD. Do all related investigative/corrective actions before further flight by doing all applicable actions specified in the service bulletin; except as required by paragraphs (i) and (l) of this AD. Repeat the inspection at intervals not to exceed 2,500 flight hours, except as required by paragraph (h) of this AD.

(1) If any vibration was reported during the time period specified in paragraph (f) of this AD, inspect within 2 days after the records review.

(2) If no vibration was reported during the time period specified in paragraph (f) of this AD, except as required by paragraph (h) of this AD, inspect before the later of:

(i) 2,500 total accumulated flight hours.

(ii) 600 flight hours or 500 flight cycles, whichever occurs first, after December 23, 2005.

Note 1: For the purposes of this AD, a detailed inspection is: “An intensive examination of a specific item, installation, or assembly to detect damage, failure, or irregularity. Available lighting is normally supplemented with a direct source of good lighting at an intensity deemed appropriate. Inspection aids such as a mirror, magnifying lenses, etc., may be necessary. Surface cleaning and elaborate procedures may be required.”

(h) If any vibration from the tail section or rudder pedals is reported after December 23, 2005, do the inspection specified in paragraph (g) of this AD before the next flight. Repeat the inspection thereafter at intervals not to exceed 2,500 flight hours.

Note 2: EMBRAER Alert Service Bulletins 145LEG-55-A010, dated August 26, 2005; and 145-55-A036, Revision 01, dated September 5, 2005; refer to EMBRAER Service Bulletins 145LEG-55-0008, Revision 01, dated January 14, 2005; 145LEG-55-0009, dated June 21, 2004; and 145-55-0034, Revision 01, dated January 14, 2005; as additional sources of service information for installing washers in the rudder II hinge fittings and control rod assembly.

(i) Where EMBRAER Alert Service Bulletins 145LEG-55-A010 and 145-55-A036 specify to contact EMBRAER for repair instructions, operators must perform the repair before further flight using a method approved by either the Manager, International Branch, ANM-116, Transport Airplane Directorate, FAA; or the Departmento de Aviacao Civil (or its delegated agent).

(j) Although EMBRAER Alert Service Bulletins 145LEG-55-A010 and 145-55-A036 recommend sending a report of the inspection results to the manufacturer, this AD does not require a report.

For Model -135ER, -135KE, -135KL, -135LR, -145, -145ER, -145MR, -145LR, -145XR, -145MP, and -145EP airplanes: Accomplishment of the inspection and applicable related investigative/corrective actions before December 23, 2005, in accordance with EMBRAER Alert Service Bulletin 145-55-A036, dated August 20, 2005, is acceptable for compliance with the corresponding requirements of this AD.

As of the effective date of this AD, use only the Accomplishment Instructions of EMBRAER Alert Service Bulletin 145LEG-55-A010, Revision 02, dated May 16, 2006 (for Model EMB-135BJ airplanes); or 145-55-A036, Revision 03, dated May 16, 2006 (for all other airplanes); as applicable; to do the actions required by paragraphs (g) and (h) of this AD, until the actions required by paragraph (m) of this AD are done.

Note 3: EMBRAER Alert Service Bulletin 145LEG-55-A010, Revision 02, dated May 16, 2006 (for Model EMB-135BJ airplanes) refers to EMBRAER Service Bulletins 145LEG-55-0008, Revision 02, dated May 26, 2006; and 145LEG-55-0009, Revision 01, dated November 23, 2005; as additional sources of service information for installing washers in the rudder II hinge fittings and control rod assembly.

Note 4: EMBRAER Alert Service Bulletin 145-55-A036, Revision 03, dated May 16, 2006 (for EMB-135ER, -135KE, -135KL, -135LR, -145, -145ER, -145MR, -145LR, -145XR, -145MP, and -145EP airplanes), refers to EMBRAER Service Bulletins 145-55-0034, Revision 02, dated May 25, 2006; and 145-55-0035, Revision 02, dated March 28, 2006; as additional sources of service information for installing washers in the rudder II hinge fittings and control rod assembly.

Within 5,500 flight hours or 36 months after the effective date of this AD, whichever occurs first, replace the locking tab washers on the control rods of the rudder II and install springs on the hinge assemblies of the rudder II, in accordance with the Accomplishment Instructions of EMBRAER Service Bulletin 145LEG-55-0011, Revision 01, dated January 23, 2007 (for Model EMB-135BJ airplanes); or 145-55-0038, Revision 01, dated January 23, 2007 (for all other airplanes); as applicable. Accomplishment of the replacement and installation constitutes terminating action for the requirements of this AD.

Actions done before the effective date of this AD in accordance with the Accomplishment Instructions of EMBRAER Service Bulletin 145LEG-55-0011, dated May 12, 2006 (for Model EMB-135BJ airplanes); or 145-55-0038, dated May 12, 2006 (for all other airplanes); as applicable; are acceptable for compliance with the requirements of paragraph (m) of this AD.