AD 2016-21-07 Airworthiness Directives; Honeywell International Inc. Turboprop Engines

This AD applies to all Honeywell International Inc. (Honeywell) TPE331-1, -2, -2UA, -3U, -3UW, -5, -5A, -5AB, -5B, -6, -6A, -10, -10AV, -10GP, -10GT, -10P, -10R, -10T, -10U, -10UA, -10UF, -10UG, -10UGR, -10UR, -11U, -12JR, -12UA, -12UAR, and -12UHR turboprop engines with Woodward fuel control unit (FCU) assemblies with Honeywell part numbers (P/Ns) as listed in Table 1 to paragraph (c) of this AD, installed. Table 1 to Paragraph ( c )—Affected FCU Assembly P/Ns Group # Engine FCU Assembly P/Ns 1 TPE331-1, -2, and -2UA P/N 869199-13, -20, -21, -22, -23, -24, -25, -26, -27, -28, -29, -31, -32, -33, -34, and -35. 2 TPE331-1, -2, and -2UA P/N 869199-9, -10, -11, -12, -14, -16, -17, and -18. 3 TPE331-3U, -3UW, -5, -5A, -5AB, -5B, -6, -6A, -10AV, -10GP, -10GT, -10P, and -10T P/N 893561-7, -8, -9, -10, -11, -14, -15, -16, -20, -26, -27, -29; and P/N 897770-1, -3, -7, -9, -10, -11, -12, -14, -15, -16, -25, -26, and -28. 4 TPE331-3U, -3UW, -5, -5B, -6, -6A, and -10T P/N 893561-4, -5, -12, -13; and P/N 897770-5, -8, and -13. 5 TPE331-10, -10R, -10U, -10UA, -10UF, -10UG, -10UGR, -10UR, -11U, -12JR, -12UA, -12UAR, and -12UHR P/N 897375-2, -3, -4, -5, -8, -9, -10, -11, -12, -13, -14, -15, -16, -17, -19, -21, -24, -25, -26, -27; and P/N 897780-1, -2, -3, -4, -5, -6, -7, -8, -9, -10, -11, -14, -15, -16, -17, -18, -19, -20, -21, -22, -23, -24, -25, -26, -27, -30, -32, -34, -36, -37, -38; and P/N 893561-17, -18, and -19.

Replacing the affected FCU assembly with an FAA-approved FCU assembly not listed in this AD by P/N is terminating action for the initial and repetitive inspections required by this AD, and for inserting the information in Figure 1 to paragraph (e) of this AD into the AFM, POH, and MOM.

For the purposes of this AD: (1) The “fuel control drive” is a series of mating splines located between the fuel pump and fuel control governor. (2) The fuel control drive consists of four drive splines: The fuel pump internal spline, the fuel control external “quill shaft” spline, and the stub shaft internal and external splines.

Comply with this AD within the compliance times specified, unless already done. (1) Inspection of Engines With FCU Assembly P/Ns in Groups 2 or 4 For FCU assembly P/Ns in Groups 2 or 4 listed in Table 1 to paragraph (c) of this AD: (i) At the next scheduled inspection of the fuel control drive, or within 500 hours-in-service (HIS) after the effective date of this AD, whichever occurs first, inspect the fuel control drive for wear. (ii) Thereafter, reinspect the fuel control drive within every 1,000 HIS since-last-inspection (SLI). (2) Inspection of Engines With FCU Assembly P/Ns in Groups 1, 3, or 5 For FCU assembly P/Ns in Groups 1, 3, or 5 listed in Table 1 to paragraph (c) of this AD: (i) If, on the effective date of this AD, the FCU assembly has 900 or more HIS SLI, inspect the fuel control drive for wear within 100 HIS after the effective date of this AD. (ii) If, on the effective date of this AD, the FCU assembly has fewer than 900 HIS SLI, inspect the fuel control drive for wear within 1,000 HIS. (iii) Thereafter, reinspect the fuel control drive for wear within every 1,000 HIS SLI. (3) Airplane Operating Procedures Within 60 days after the effective date of this AD, insert the information in Figure 1 to paragraph (e) of this AD, into the Emergency Procedures Section of the applicable Airplane Flight Manual (AFM), Pilot Operating Handbook (POH), or the Manufacturer's Operating Manual (MOM). BILLING CODE 4910-13-P ER24OC16.000 BILLING CODE 4910-13-C

This AD replaces AD 2015-12-04, Amendment 39-18177, (80 FR 34534, June 17, 2015).