Airworthiness Directive · Amendment 39-18419 · Fuselage
Piper Aircraft, Inc. Airplanes
This AD applies to the following Piper Aircraft, Inc. airplanes listed in paragraphs (c)(1) and (c)(2) of this AD, certificated in any category:
(1) Models PA-31, PA-31-300, and PA-31-325: Serial numbers 31-2 through 31-900 and 31-7300901 through 31-8312019; and
(2) Model PA-31-350: Serial numbers 31-5001 through 31-5004 and 31-7305005 through 31-8553002.
Note 1 to paragraph (c)(1) of this AD: The Model PA-31 may also be identified as a PA-31-310, even though the PA-31-310 is not a model recognized by the Federal Aviation Administration (FAA) on the type certificate data sheet.
We are superseding Airworthiness Directive (AD) 96-12-12, which applies to certain Piper Aircraft, Inc. Models PA-31, PA-31-300, PA-31-325, and PA-31-350 airplanes. AD 96-12-12 requires a one-time inspection of the bulkhead assembly at fuselage station (FS) 317.75 for cracks and the installation of one of two reinforcement kits determined by whether cracks were found during the inspection. This new AD requires repetitive inspections of the bulkhead assembly at FS 317.75 for cracks, repair of cracks as necessary, and the installation of a reinforcement modification. This AD was prompted by cracks found in the FS 317.75 upper bulkhead. We are issuing this AD to correct the unsafe condition on these products.
(1) Before or upon accumulating 2,000 hours time-in-service (TIS) or within the next 100 hours TIS after April 15, 2016 (the effective date of this AD), whichever occurs later, and repetitively thereafter at intervals not to exceed 100 hours TIS, inspect the bulkhead assembly at FS 317.75 for cracks following Part I of the Instructions in Piper Aircraft, Inc. Service Bulletin No. 1273A, dated October 22, 2015.
(2) If any cracks are found during the inspection required in paragraph (g)(1) of this AD, before further flight, repair the cracks and install the reinforcement modification following Part I of the Instructions in Piper Aircraft, Inc. Service Bulletin No. 1273A, dated October 22, 2015. This repair/modification terminates the requirements for the repetitive inspections required in paragraph (g)(1) of this AD.
(3) You may do the modification required in paragraph (h) of this AD to terminate the repetitive inspections required in paragraph (g)(1) of this AD.
Unless already done as a repair for cracks found in the inspection required in paragraph (g)(1) of this AD, before or upon accumulating 2,500 hours TIS or within the next 500 hours after April 15, 2016 (the effective date of this AD), whichever occurs later, install the reinforcement modification following Part II of the Instructions in Piper Aircraft, Inc. Service Bulletin No. 1273A, dated October 22, 2015. This modification terminates the repetitive inspections required in paragraph (g)(1) of this AD.
This AD allows credit for the inspection required in paragraph (g)(1) of this AD and the repair required in paragraph (g)(2) of this AD, if done before April 15, 2016 (the effective date of this AD), following Part I of the Instructions in Piper Aircraft, Inc. Service Bulletin No. 1273, dated June 4, 2015. This AD also allows credit for the modification required in paragraph (h) of this AD, if done before April 15, 2016 (the effective date of this AD), following Part II of the Instructions in Piper Aircraft, Inc. Service Bulletin No. 1273, dated June 4, 2015.
The aircraft, engines and makers this AD names, by the model designations in its text. A model listed here may still be outside the AD's serial ranges.
