Airworthiness Directive · Amendment 39-11956 · 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
Model EMB-135 and EMB-145 series airplanes, certificated in any category, as listed in Embraer Service Bulletin 145-55-0022, Change 02, dated May 4, 2000, or Embraer Service Bulletin 145-55-0024, dated May 25, 2000; and those airplanes on which the elevator servo tabs and spring tabs have been replaced in accordance with Embraer Alert Service Bulletin 145-55-A022, Change 02, dated October 8, 1999, or Embraer Service Bulletin 145-55-0022, dated October 20, 1999.
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 (e)(1) 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 supersedes an existing airworthiness directive (AD), applicable to certain EMBRAER Model EMB-135 and EMB-145 series airplanes, that currently 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 clarifies certain fiberscopic inspection and replacement procedures, and corrective actions; revises the applicability of the existing AD; and adds an inspection procedure for the servo tab center hinge fittings to detect the presence of washers for both attaching fasteners, and follow-on corrective actions, if necessary. This amendment also provides for optional terminating action for the repetitive inspections. 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 disconnection of the elevator spring tab or servo tab hinge from their attachments, which could result in loss of elevator control and reduced controllability of the airplane, accomplish the following:
(a) Within 20 flight hours after the effective date of this AD, perform a detailed visual inspection of the hinge fittings of the left and right elevator spring tabs and servo tabs to detect any discrepancy (including incorrect attachment of the hinge fittings; signs of scratches on painted surfaces of the tab spar; detachment of hinge fitting from the tab; and relative movement and gap between hinge fittings and tab spars, and between the spring tab spar or skin) in accordance with Part I of the Accomplishment Instructions of Embraer Service Bulletin (S.B.) 145-55-0024, dated May 25, 2000.
Note 2: Inspections accomplished prior to the effective date of this amendment, in accordance with Part I of the Accomplishment Instructions of S.B. 145-55-0022, dated October 20, 1999, or Change 01, dated January 25, 2000, or alert S.B. 145-55-A022, Change 02, dated October 8, 1999, are considered acceptable for compliance with the requirements of paragraph (a) of this AD.
(1) If no discrepancy is detected, repeat the detailed visual inspection thereafter at intervals not to exceed 100 flight hours until accomplishment of either paragraph (b) or (c) of this AD.
(2) If any discrepancy is detected, prior to further flight, accomplish the action specified by either paragraph (a)(2)(i) or (a)(2)(ii) of this AD.
(i) Replace any discrepant elevator tab with a new tab in accordance with the service bulletin, and repeat the detailed visual inspection thereafter at intervals not to exceed 100 flight hours until accomplishment of either the actions required by paragraph (b) or the optional terminating action specified by paragraph (c) of this AD.
Note 3: The inspection and fastener replacement actions required by paragraph (b) of this AD do not constitute terminating action for the requirements of this AD, but only extend the inspection intervals from 100 to 400 flight hours.
(ii) Perform the optional terminating action specified by paragraph (c) of this AD.
Note 4: 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 mirror, magnifying lenses, etc. may be used. Surface cleaning and elaborate access procedures may be required.”
(b) Within 400 flight hours after the effective date of this AD, perform a one-time detailed visual inspection, using a fiberscope, of the servo tab center hinge fitting to the tab skin to detect any discrepancy (including the absence of washers under the collar bases of both attaching fasteners, and incorrect fastener connection) in accordance with Part II of the Accomplishment Instructions of S.B. 145-55-0024, dated May 25, 2000.
(1) If no discrepancy is detected, repeat the inspection required by paragraph (a) of this AD thereafter at intervals not to exceed 400 flight hours until accomplishment of the optional terminating action specified by paragraph (c) of this AD.
(2) If any discrepancy is detected, prior to further flight, replace, one at a time, each affected fastener with a new fastener having a washer, in accordance with the service bulletin. Repeat the inspection required by paragraph (a) of this AD thereafter at intervals not to exceed 400 flight hours until accomplishment of the optional terminating action specified by paragraph (c) of this AD.
Note 5: Replacement of the attaching fasteners one at a time will avoid the loss of the servo tab or spring tab hinge fittings position.
(c) Rework (including installation of the elevator servo and spring tabs; and reidentification, static balancing, and installation of the elevator) of all elevator servo and spring tabs in accordance with Part III of the Accomplishment Instructions of S.B. 145-055-0022, Change 02, dated May 4, 2000, constitutes terminating action for the repetitive inspections required by this AD. Model EMB-135 and EMB-145 series airplanes having serial numbers 145004 through 145043, must accomplish the modifications specified by S.B. 145-27-0034, Change 01, dated August 5, 1998, prior to the rework specified by this paragraph.
Note 6: Modifications of certain airplanes specified in paragraph (c) of this AD, accomplished before the effective date of this amendment, in accordance with S.B. 145-27-0034, dated April 3, 1998, are considered acceptable for compliance with the modification requirement in paragraph (c) of this AD.
(d) Submit a report of inspection findings for any discrepancy detected during any inspection required by paragraph (a) of this AD to Empresa Brasileira de Aeronautica S.A. (EMBRAER), P.O. Box 343—CEP 12.225, Sao Jose dos Campos—SP, Brazil; at the applicable time specified in paragraph (d)(1) or (d)(2) of this AD. Information collection requirements contained in this regulation have been approved by the Office of Management and Budget (OMB) under the provisions of the Paperwork Reduction Act of 1980 (44 U.S.C. 3501 et seq.) and have been assigned OMB Control Number 2120-0056.
(1) For airplanes on which any inspection is accomplished after the effective date of this AD: Submit the report within 10 days after performing any detailed visual inspection required by paragraph (a) of this AD.
(2) For airplanes on which any inspection has been accomplished prior to the effective date of this AD: Submit the report within 10 days after the effective date of this AD.
(e)(1) 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 Maintenance Inspector, who may add comments and then send it to the Manager, Atlanta ACO.
(2) Alternative methods of compliance, approved previously in accordance with AD 2000-04-09, amendment 39-11591, are approved as alternative methods of compliance with this AD.
Note 7: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Atlanta ACO.
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.
