Looks like the FAA only focused on GE engines, even though the Trent was specifically mentioned in non-FAA documents as not being immune to a similar condition... here is some germane snips from the prior A/D for PS3 tube issues:
Federal Aviation Administration 14 CFR Part 39
[Docket No. 99-NE-62-AD; Amendment 39-12473; AD 2001-21-03]
RIN 2120-AA64
Airworthiness Directives; General Electric Company GE90 Series Turbofan Engines
...the FAA is especially concerned about the possibility of simultaneous loss of thrust control on both engines due to ice blockage of each engine's Ps3 pressure sensing system under certain atmospheric conditions. Corruption of Ps3 signals could result in simultaneous loss of thrust control of both engines. The unsafe condition description is rewritten for clarification as follows: "The actions specified in this AD are intended to prevent corruption of Ps3 signals, which could result in simultaneous loss of thrust control of both engines."
Remove Reference to P3B Signal Blockage From Unsafe Condition Description
One comment from the manufacturer requests that the unsafe condition statement in the AD be revised to remove P3B signal blockage and partial blockage as some of the causes of loss of engine thrust control. Blockage and partial blockage of the P3B signal could result in a change to the engine acceleration schedule, and possibly a reduction in compressor stall margin, but a loss of thrust control would not occur. The FAA agrees. Reference to P3B signal blockage and partial blockage is removed from the unsafe condition statement in this AD.
http://rgl.faa.gov/Regulatory_and_Gu...4?OpenDocument
http://www8.landings.com/cgi-bin/get...001-21-03.html
NOTES: Addtl info:
Ps3 compressor discharge static pressure, lbf/in2 ~(50-500)
PS3 (or P3 or PT3)= Pressure (& temp) at engine Station 3 (3.0). Compressor discharge pressure.
Both Ps3 and P3B pressure systems incorporate weep holes that allows drainage of water in the lines that may accumulate from condensation or ingested water; however, the field events and the investigation have determined that these design features may not always be effective in eliminating water from these systems. GE is assessing design changes that will prevent water from freezing in these systems and causing corruption of the signals to the FADEC.
Second A/D:
Federal Aviation Administration
14 CFR Part 39 [66 FR 8165 1/30/2001]
[Docket No. 2001-NE-03-AD; Amendment 39-12097; AD 2001-02-12]
RIN 2120-AA64
Airworthiness Directives; CFM International (CFMI) model CFM56-7B Turbofan Engines
AGENCY: Federal Aviation Administration, DOT.
ACTION: Final rule; request for comments.
SUMMARY: This amendment adopts a new airworthiness directive (AD) that is applicable to CFMI model CFM56-7B turbofan engines. This action requires a one-time on-wing torque inspection, and torque if needed, of all the PS3 pressure line fittings to insure proper torque. This amendment is prompted by service events which resulted in two in-flight shutdowns (IFSD’s) and an aborted takeoff due to the disconnection of one of the PS3 line fittings. The actions specified in this AD are intended to prevent air leakage from incorrectly torqued fittings of the PS3 line, which could result in engine power loss.
DATES: Effective February 14, 2001.