Airworthiness Directive · Amendment 39-11591 · Empresa Brasileira de Aeronautica S.A. (EMBRAER) Model EMB-135 and EMB-145 Series Airplanes
Empresa Brasileira de Aeronautica S.A. (EMBRAER) Model EMB-135 and EMB-145 Series Airplanes
Superseded. A later AD replaced this one: AD 2000-22-10. Comply with the one in force.
Model EMB-135 and EMB-145 series airplanes, as listed in Embraer Alert Service Bulletin S.B. 145-55-A022, Change 02, dated October 8, 1999; certificated in any category.
Note 1: This AD applies to each airplane identified in the preceding applicability provision, regardless of whether it has been 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 adopts a new airworthiness directive (AD) that is applicable to certain EMBRAER Model EMB-135 and EMB-145 series airplanes. This action requires various inspections to detect discrepancies of the elevator servo tab and spring tab hinge fittings of the horizontal stabilizer, and follow-on corrective actions, if necessary. This amendment is prompted by issuance of mandatory continuing airworthiness information by a foreign civil airworthiness authority. The actions specified in this AD are intended to prevent the linkage of the elevator servo tab or spring tab hinge fittings from separating from the horizontal stabilizer, which could result in loss of control of the airplane.
To prevent the linkage of the elevator servo tab or spring tab hinge fittings from separating from the horizontal stabilizer, which could result in loss of control of the airplane, accomplish the following:
(a) Within 10 flight hours after the effective date of this AD, perform a detailed visual inspection to verify proper attachment, as specified in the alert service bulletin, of the left- and right-hand elevator servo tab and spring tab hinge fittings of the horizontal stabilizer, in accordance with Part I of the Accomplishment Instructions of Embraer Alert Service Bulletin S.B. 145-55-A022, Change 02, dated October 8, 1999.
Note 2: For the purposes of this AD, a detailed visual inspection is defined as: “An intensive visual examination of a specific structural area, system, installation, or assembly to detect damage, failure, or irregularity. Available lighting is normally supplemented with a direct source of good lighting at intensity deemed appropriate by the inspector. Inspection aids such as mirrors, magnifying lenses, etc., may be used. Surface cleaning and elaborate access procedures may be required.”
(1) If all elevator servo tab and spring tab hinge fittings are properly attached, as specified in the alert service bulletin, repeat the detailed visual inspection thereafter at intervals not to exceed 100 flight hours until the requirements of paragraph (b) of this AD are accomplished.
(2) If any elevator servo tab or spring tab hinge fitting is improperly attached, as specified in the alert service bulletin, prior to further flight, accomplish the requirements of either paragraph (a)(2)(i) or (a)(2)(ii) of this AD.
(i) Replace the affected tab with a new or serviceable tab in accordance with Part I of the Accomplishment Instruction of the alert service bulletin. Thereafter, repeat the detailed visual inspection required by paragraph (a) of this AD at intervals not to exceed 100 flight hours until the requirements of paragraph (b) of this AD are accomplished. Following replacement of all tabs, repeat the inspection required by paragraph (a) of this AD at intervals not to exceed 400 flight cycles; or
(ii) Accomplish the requirements of paragraphs (b) of this AD.
(b) For airplanes that have not replaced all elevator servo tabs and spring tabs: Within 400 flight hours after the effective date of this AD, perform a one-time detailed visual inspection to detect relative movement between the servo tab center hinge fitting and the tab lower skin and tab spar, and between the elevator spring tab inboard hinge fitting and the tab upper skin and tab spar, in accordance with Part II of the Accomplishment Instructions of Embraer Alert Service Bulletin S.B. 145-55-A022, Change 02, dated October 8, 1999.
(1) If no relative movement is detected, prior to further flight, rework the elevator servo tabs and spring tabs and perform a boroscopic inspection to verify correct installation, as specified in the alert service bulletin, of the fasteners attaching the elevator servo tab and spring tab hinge fittings to the elevator servo tab and spring tab, in accordance with Part II of the Accomplishment Instruction of the alert service bulletin.
(i) If all fasteners attaching the elevator servo tab and spring tab hinge fittings are installed correctly, repeat the inspection required by paragraph (a) of this AD at intervals not to exceed 400 flight cycles.
(ii) If any fastener attaching the elevator servo tab or spring tab hinge fittings is incorrectly installed, as specified in the alert service bulletin, prior to further flight, replace, one at a time, each affected fastener with a new fastener and washer, and prior to further flight, repeat the boroscopic inspection required by paragraph (b)(1) of this AD. When correct fastener installation is verified, repeat the inspection required by paragraph (a) of this AD at intervals not to exceed 400 flight cycles.
Note 3: Replacement of the attaching fasteners one at a time will avoid the loss of the servo tab or spring tab hinge fittings position.
(2) If any relative movement is detected, prior to further flight, replace the affected tab with a new or serviceable tab, in accordance with Part II of the Accomplishment Instructions of the alert service bulletin. Following replacement of all tabs, repeat the inspection required by paragraph (a) of this AD at intervals not to exceed 400 flight cycles.
Note 4: Accomplishment of the actions required by this AD prior to the effective date of this AD, in accordance with Embraer Alert Service Bulletin S.B. 145-55-A022, dated September 24, 1999, or Revision 01, dated October 7, 1999, is considered acceptable for the compliance with the applicable actions specified by this AD.
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
