Airworthiness Directive · Amendment 39-17650 · Fuselage
Empresa Brasileira de Aeronautica S.A. (EMBRAER) Airplanes
This AD applies to Empresa Brasileira de Aeronautica S.A. (EMBRAER) Model EMB-135ER, -135KE, -135KL, and -135LR airplanes, and Model EMB-145, -145ER, -145MR, -145LR, -145XR, -145MP, and -145EP airplanes, certificated in any category, as identified in EMBRAER Service Bulletin 145-53-0082, dated October 18, 2013.
We are adopting a new airworthiness directive (AD) for certain Empresa Brasileira de Aeronautica S.A. (EMBRAER) Model EMB-135ER, - 135KE, -135KL, and -135LR airplanes; and Model EMB-145, -145ER, -145MR, -145LR, -145XR, -145MP, and -145EP airplanes. This AD requires repetitive detailed inspections to detect discrepancies on the attaching parts of the lower eyelet fitting of the cockpit windshield center-post, and, if no discrepancy is found, a check to make sure the bolts are tight, and replacement of the attaching parts if necessary. This AD also provides an option to accomplish the replacement of the attaching parts, which terminates the repetitive inspections. This AD was prompted by reports of failure of the bolts that connect the lower eyelet fitting of the cockpit windshield center-post to the forward fuselage. We are issuing this AD to detect and correct failed bolts and attaching parts of the lower eyelet fitting of the cockpit windshield center-post, which could lead to loss of structural integrity of the airplane.
You are responsible for having the actions required by this AD performed within the compliance times specified, unless the actions have already been done.
(1) For Group 1 airplanes, as identified in EMBRAER Service Bulletin 145-53-0082, dated October 18, 2013: At the applicable compliance time specified in paragraph (g)(1)(i), (g)(1)(ii), (g)(1)(iii), or (g)(1)(iv) of this AD, do a detailed inspection to detect discrepancies on the attaching parts of the lower eyelet fitting of the cockpit windshield center-post, and if no discrepancy is found, before further flight, do a check to make sure the bolts are tight, in accordance with the Accomplishment Instructions of EMBRAER Service Bulletin 145-53-0082, dated October 18, 2013. Repeat the actions required by this paragraph thereafter at intervals not to exceed 500 flight cycles until the accomplishment of the replacement required by paragraph (h) of this AD or the optional terminating action specified in paragraph (i) of this AD.
(i) For airplanes with 11,000 total flight cycles or more as of the effective date of this AD: Do the inspection within 50 flight cycles after the effective date of this AD.
(ii) For airplanes with 10,000 total flight cycles or more but fewer than 11,000 total flight cycles as of the effective date of this AD: Do the inspection before the accumulation of 11,050 total flight cycles, or within 150 flight cycles after the effective date of this AD, whichever occurs first.
(iii) For airplanes with 7,500 total flight cycles or more but fewer than 10,000 total flight cycles as of the effective date of this AD: Do the inspection before the accumulation of 10,150 total flight cycles, or within 500 flight cycles after the effective date of this AD, whichever occurs first.
(iv) For airplanes with fewer than 7,500 total flight cycles as of the effective date of this AD: Do the inspection before the accumulation of 8,000 total flight cycles, or within 5,000 flight cycles after the effective date of this AD, whichever occurs first.
(2) For Group 2 airplanes, as identified in EMBRAER Service Bulletin 145-53-0082, dated October 18, 2013 (airplanes on which the actions specified in EMBRAER Service Bulletin 145-53-0058, dated December 23, 2004; or Revision 01, dated March 30, 2007; have been done): At the applicable compliance time specified in paragraph (g)(2)(i), (g)(2)(ii), (g)(2)(iii), or (g)(2)(iv) of this AD, do a detailed inspection to detect discrepancies on the attaching parts of the lower eyelet fitting of the cockpit windshield center-post, and if no discrepancy is found, before further flight, do a check to make sure the bolts are tight, in accordance with the Accomplishment Instructions of EMBRAER Service Bulletin 145-53-0082, dated October 18, 2013. Repeat the actions required by this paragraph thereafter at intervals not to exceed 500 flight cycles until the accomplishment of the requirements of paragraph (h) of this AD or the optional terminating action specified in paragraph (i) of this AD.
(i) For airplanes that, as of the effective date of this AD, have accumulated 11,000 flight cycles or more since the incorporation of the actions specified in EMBRAER Service Bulletin 145-53-0058: Do the inspection within 50 flight cycles after the effective date of this AD.
(ii) For airplanes that, as of the effective date of this AD, have accumulated 10,000 flight cycles or more but fewer than 11,000 flight cycles since the incorporation of the actions specified in EMBRAER Service Bulletin 145-53-0058: Do the inspection within 11,050 flight cycles after the incorporation of the actions specified in EMBRAER Service Bulletin 145-53-0058, or within 150 flight cycles after the effective date of this AD, whichever occurs first.
(iii) For airplanes that, as of the effective date of this AD, have accumulated 7,500 flight cycles or more but fewer than 10,000 flight cycles since the incorporation of the actions specified in EMBRAER Service Bulletin 145-53-0058: Do the inspection within 10,150 flight cycles after the incorporation of the actions specified in EMBRAER Service Bulletin 145-53-0058, or within 500 flight cycles after the effective date of this AD, whichever occurs first.
(iv) For airplanes that, as of the effective date of this AD, accumulated fewer than 7,500 flight cycles since the incorporation of the actions specified in EMBRAER Service Bulletin 145-53-0058: Do the inspection within 8,000 flight cycles after the incorporation of the actions specified in EMBRAER Service Bulletin 145-53-0058, or within 5,000 flight cycles after the effective date of this AD, whichever occurs first.
If, during any inspection required by paragraph (g) of this AD, any discrepancy is found or if, during any check required by paragraph (g) of this AD, any bolt is found that is not tight, before further flight, do the replacement of the attaching parts of the lower eyelet fitting of the cockpit windshield center-post, including doing a general visual inspection for damage on the eyelet fitting; in accordance with the Accomplishment Instructions of EMBRAER Service Bulletin 145-53-0082, dated October 18, 2013. If any damage to the eyelet fitting is found, before further flight, repair using a method approved by the Manager, International Branch, ANM-116, Transport Airplane Directorate, FAA; or Agência Nacional de Aviação Civil (ANAC) (or its delegated agent, or by the Design Approval Holder (DAH) with ANAC design organization approval). For a repair method to be approved, the repair approval must specifically refer to this AD.
For Group 1 airplanes, and Group 2 airplanes (airplanes on which the actions specified in EMBRAER Service Bulletin 145-53-0058, dated December 23, 2004; or Revision 01, dated March 30, 2007; have been done), as identified in EMBRAER Service Bulletin 145-53-0082, dated October 18, 2013: Doing the replacement of the attaching parts of the lower eyelet fitting of the cockpit windshield center-post, including doing a general visual inspection for damage on the eyelet fitting if any discrepancy is found in any bolts, terminates the inspections required by paragraph (g) of this AD. The replacement specified in this paragraph must be done in accordance with the Accomplishment Instructions of EMBRAER Service Bulletin 145-53-0082, dated October 18, 2013, except as required by paragraph (j) of this AD.
Where EMBRAER Service Bulletin 145-53-0082, dated October 18, 2013, specifies to contact Embraer if there are signs of damage on the eyelet fitting, before further flight, repair using a method approved by the Manager, International Branch, ANM-116, Transport Airplane Directorate, FAA; or ANAC (or its delegated agent, or by the DAH with ANAC design organization approval). For a repair method to be approved, the repair approval must specifically refer to 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.
