Is AD E6-17327 a recurring Airworthiness Directive?

No — AD E6-17327 is a one-time directive. Verify it was complied with in the aircraft's records.

Which aircraft does AD E6-17327 apply to?

AD E6-17327 applies to Pratt & Whitney — models JT8D-1, JT8D-1A, JT8D-1B, JT8D-7, JT8D-7A, JT8D-7B, JT8D-9, JT8D-9A. Serial/part conditions may narrow it to specific aircraft.

Airworthiness Directive E6-17327

one-time

AD E6-17327 · 2006-10-18 · turbine engine

Airworthiness Directives; Pratt & Whitney JT8D-1, -1A, -1B, -7, -7A, -7B, -9, -9A, -11, -15, -15A, -17, -17A, -17R, -17AR, -209, -217, -217A, -217C, and -219 Turbofan Engines

What this AD requires

The FAA is revising an existing airworthiness directive (AD) for Pratt & Whitney (PW) JT8D-1, -1A, -1B, -7, -7A, -7B, -9, -9A, -11, -15, -15A, -17, -17A, -17R, -17AR, -209, -217, -217A, -217C, and -219 turbofan engines. That AD currently requires either replacing high pressure compressor (HPC) front hubs and HPC disks that have operated at any time with PWA 110-21 coating and that operated in certain engine models, or, visually inspecting and fluorescent penetrant inspecting (FMPI) for cracking of those parts and re-plating them if they pass inspection. This AD requires the same actions, but makes necessary corrections to inadvertent reference errors and omissions found in AD 2006-17-07, and relaxes some of the compliance times in Table 5. This AD results from our finding reference errors and omissions in AD 2006- 17-07, from determining that the AD as drafted imposed an unnecessary burden on operators if they have to immediately remove engines, and from requests to clarify compliance paragraphs. We are issuing this AD to prevent a rupture of an HPC front hub or an HPC disk that could result in an uncontained engine failure and damage to the airplane.

Which aircraft AD E6-17327 applies to

MakesPratt & Whitney

ModelsJT8D-1, JT8D-1A, JT8D-1B, JT8D-7, JT8D-7A, JT8D-7B, JT8D-9, JT8D-9A, JT8D-11, JT8D-15, JT8D-15A, JT8D-17, JT8D-17A, JT8D-17R, JT8D-17AR, JT8D-209, JT8D-217, JT8D-217A, JT8D-217C, JT8D-219, JT8D

Applicability keyed to 8th stage HPC front hub coating (PWA 110-21 or Nickel-Cadmium) combined with the stage 8-9 spacer coating and the specific engine model, per the applicability matrix in Table 1 of the AD. Installed on, but not limited to, Boeing DC-9, MD-80 series, 727 series, and 737 series airplanes. Issued to correct reference errors/omissions in AD 2006-17-07.

Whether AD E6-17327 actually applies to your aircraft (by serial and installed parts) and whether it’s already complied with comes from that aircraft’s records.

How AD compliance is recorded

A valid compliance record (14 CFR 43.9) states:

Method of compliance — The specific action taken (inspected, replaced, modified) and to what revision.

Date — When the work was done.

Aircraft time — Total time in service / tach at compliance — how recurring next-due is computed.

Signature & certificate — The A&P/IA who returned it to service, with certificate number.

Is AD E6-17327 complied with on your aircraft?

Tailplate reads a tail number’s logbooks and matches every applicable AD — including this one — to its compliance evidence, with recurring next-due dates computed.

Look up a tail number →Read the full directive (Federal Register)

Applicability is derived from the FAA directive corpus and is advisory, not a legal airworthiness determination. Compliance is established only from an aircraft’s actual records.