AD 2014-16-16 Airworthiness Directives; Empresa Brasileira de Aeronautica S.A. (Embraer) Airplanes

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

This AD applies to all Embraer S.A. Model ERJ 190-100 STD, -100 LR, -100 ECJ, -100 IGW, -200 STD, -200 LR, and -200 IGW airplanes, certificated in any category.

Comply with this AD within the compliance times specified, unless already done.

Retorque the left and right pylon outboard and inboard lower link fittings, as specified in paragraph (g)(1) or (g)(2) of this AD, as applicable. (1) For airplanes identified as Groups 1 and 2 in Embraer Service Bulletin 190-54-0015, dated July 3, 2014: Retorque at the applicable time specified in paragraph (g)(1)(i) or (g)(1)(ii) of this AD, in accordance with the Accomplishment Instructions of Embraer Alert Service Bulletin 190-54-A015, Revision 03, dated June 27, 2014. (i) For Group 1 airplanes: Retorque at the applicable time specified in paragraph (g)(1)(i)(A) or (g)(1)(i)(B) of this AD. (A) If, as of the effective date of this AD, the airplane has accumulated fewer than 600 total flight cycles and less than 750 total flight hours since accomplishment of the actions specified in Embraer Service Bulletin 190-54-0013: Retorque within 50 flight hours after the effective date of this AD. (B) If, as of the effective date of this AD, the airplane has accumulated 600 or more total flight cycles or 750 or more total flight hours after accomplishment of Embraer Service Bulletin 190-54-0013: Retorque within 10 flight hours after the effective date of this AD. (ii) For Group 2 airplanes: Retorque at the applicable time specified in paragraph (g)(1)(ii)(A) or (g)(1)(ii)(B) of this AD. (A) If, as of the effective date of this AD, the airplane has accumulated fewer than 600 total flight cycles and less than 750 total flight hours: Retorque within 50 flight hours after the effective date of this AD. (B) If, as of the effective date of this AD, the airplane has accumulated 600 or more total flight cycles or 750 or more total flight hours: Retorque within 10 flight hours after the effective date of this AD. (2) For airplanes identified as Groups 1 and 2 in Embraer Service Bulletin 190LIN-54-0006, dated July 3, 2014: Retorque at the applicable time specified in paragraph (g)(2)(i) or (g)(2)(ii) of this AD, in accordance with the Accomplishment Instructions of Embraer Alert Service Bulletin 190LIN-54-A006, Revision 02, dated June 27, 2014. (i) For Group 1 airplanes: Retorque at the applicable time specified in paragraph (g)(2)(i)(A) or (g)(2)(i)(B) of this AD. (A) If, as of the effective date of this AD, the airplane has accumulated fewer than 200 total flight cycles and less than 750 total flight hours since accomplishment of the actions specified in Embraer Service Bulletin 190LIN-54-0004: Retorque within 50 flight hours after the effective date of this AD. (B) If, as of the effective date of this AD, the airplane has accumulated 200 or more total flight cycles or 750 or more total flight hours since accomplishment of the actions specified in Embraer Service Bulletin 190LIN-54-0004: Retorque within 10 flight hours after the effective date of this AD. (ii) For Group 2 airplanes: Retorque at the applicable time specified in (g)(2)(ii)(A) or (g)(2)(ii)(B) of this AD. (A) If, as of the effective date of this AD, the airplane has accumulated fewer than 200 total flight cycles and less than 750 total flight hours: Retorque within 50 flight hours after the effective date of this AD. (B) If, as of the effective date of this AD, the airplane has accumulated 200 or more total flight cycles or 750 or more total flight hours: Retorque within 10 flight hours after the effective date of this AD.

This AD was prompted by a report of a loose lower link assembly on the left and right pylons. We are issuing this AD to prevent loss of a shear pin on the pylon outboard and inboard lower link fittings, which could result in failure of the fitting and consequent separation of the engine from the wing.

None.