2012-04-05: Electronic control unit (ECU)

Adoption of the Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA amends 14 CFR part 39 as follows: PART 39--AIRWORTHINESS DIRECTIVES 0 1. The authority citation for part 39 continues to read as follows: Authority: 49 U.S.C. 106(g), 40113, 44701. Sec. 39.13 [Amended] 0 2. The FAA amends Sec. 39.13 by removing airworthiness directive (AD) 2007-12-07, Amendment 39-15085 (72 FR 31174, June 6, 2007), and adding the following new AD: 2012-04-05 General Electric Company (GE): Amendment 39-16961; Docket No. FAA-2006-25738; Directorate Identifier 2006-NE-27-AD. (a) Effective Date This airworthiness directive (AD) is effective March 30, 2012. (b) Affected ADs This AD supersedes AD 2007-12-07, Amendment 39-15085 (72 FR 31174, June 6, 2007). (c) Applicability This AD applies to GE CF6-80C2B1F, CF6-80C2B1F1, CF6-80C2B1F2, CF6-80C2B2F, CF6-80C2B3F, CF6-80C2B4F, CF6-80C2B5F, CF6-80C2B6F,CF6-80C2B6FA, CF6-80C2B7F, and CF6-80C2B8F turbofan engines, including engines marked on the engine data plate as CF6-80C2B7F1. (d) Unsafe Condition This AD results from: (1) Two reports of engine flameout events during flight in inclement weather conditions; and (2) Eight reports of engine in-flight shutdown (IFSD) events caused by dual-channel central processing unit (CPU) faults in the electronic control unit (ECU); and (3) Four reports of engine flameout ground events. (e) We are issuing this AD to prevent engine flameout or un- commanded engine IFSD of one or more engines, leading to an emergency or forced landing of the airplane. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) ECU Removal (1) Remove from service ECUs with part numbers (P/Ns) listed in Table 1 of this AD within 6 months or 450 engine flight cycles after the effective date of this AD, whichever occurs first. Table 1--Affected ECU P/Ns ---------------------------------------------------------------------------------------------------------------- ---------------------------------------------------------------------------------------------------------------- 1471M63P01 1471M63P02 1471M63P03 1471M63P04 1471M63P05 1471M63P06 1471M63P07 1471M63P08 1471M63P09 1471M63P10 1471M63P11 1471M63P12 1471M63P13 1471M63P14 1471M63P15 1471M63P16 1471M63P17 1471M63P18 1471M63P23 1471M63P24 [[Page 10952]] 1471M63P25 1471M63P26 1471M63P27 1471M63P28 1471M63P29 1471M63P30 1471M63P31 1471M63P32 1471M63P33 1471M63P34 1471M63P35 1471M63P36 1519M89P01 1519M89P021519M89P03 1519M89P04 1519M89P05 1519M89P06 1519M89P07 1519M89P08 1519M89P09 1519M89P10 1519M89P13 1519M89P14 1519M89P15 1519M89P16 1519M89P17 1519M89P18 1519M89P19 1519M89P20 1519M89P21 1519M89P22 1519M89P23 1519M89P24 1519M89P25 1519M89P26 1820M33P01 1820M33P02 1820M33P03 1820M33P04 1820M33P05 1820M33P06 1820M33P07 1820M33P08 1820M33P09 ---------------------------------------------------------------------------------------------------------------- (2) Remove from service ECUs with P/Ns 2121M37P01, 2121M37P02, 2121M38P01, 2121M38P02, 2121M41P01 and 2121M41P02 within 14 months or 1,050 engine flight cycles after the effective date of this AD, whichever occurs first.(3) Remove from service ECUs with P/Ns listed in Table 2 of this AD within 60 months or 4,500 engine flight cycles after the effective date of this AD, whichever occurs first. Table 2--Affected ECU P/Ns ---------------------------------------------------------------------------------------------------------------- ---------------------------------------------------------------------------------------------------------------- 1471M63P37 1471M63P38 1471M63P39 1471M63P40 1471M63P42 1519M89P27 1519M89P28 1519M89P29 1519M89P30 1519M89P32 1820M33P10 1820M33P11 1820M33P12 1820M33P13 1820M33P15 2121M25P01 2121M25P02 2121M26P01 2121M26P02 2121M29P01 2121M29P02 2121M37P03 2121M38P03 2121M41P03 ---------------------------------------------------------------------------------------------------------------- (h) Installation Prohibition (1) After the effective date of this AD, do not install any ECU P/N listed in Table 1 of this AD onto any airplane. (2) After the effective date of this AD, do not operate any airplane with more than one ECU P/N 2121M37P02, 2121M38P02, or 2121M41P02 installed. (i) Alternative Methods of Compliance (AMOCs) The Manager, Engine Certification Office, FAA, may approve AMOCs for this AD. Use the procedures in 14 CFR 39.19 to make your request. (j) Related Information For more information about this AD, contact Tomasz Rakowski, Aerospace Engineer, Engine Certification Office, FAA, Engine & Propeller Directorate, 12 New England Executive Park, Burlington, MA 01803; phone: 781-238-7735; fax: 781-238-7199; email: tomasz.rakowski@faa.gov. (k) Material Incorporated by Reference None.