Airworthiness Directive · Amendment 39-18495 · Engine fuel and control
Piper Aircraft, Inc. Airplanes
This AD applies to Piper Aircraft, Inc. Model PA-31-350 airplanes, serial numbers 31-5001 through 31-5004, 31-7305005 through 31-8452024, and 31-8253001 through 31-8553002, certificated in any category, that are equipped with the following engines and fuel pump hose assemblies:
| Engine | Manufacturer's hose name | Manufacturer's part No. (P/N) | Hose description |
|---|---|---|---|
| LTIO-540-J2B (right wing) | Hose Assembly—Fuel | Piper 39995-034 | Inlet fuel hose to engine fuel pump. |
| TIO-540-J2B (left wing) | Hose, Fuel pump to Injector | Lycoming LW-12877-6S142 | Exit fuel hose from engine fuel pump. |
| LTIO-540-J2BD (right wing) | Hose, Fuel pump to Injector | Lycoming LW-12877-6S142 | Exit fuel hose from engine fuel pump. |
| TIO-540-J2BD (left wing) | Hose Assembly—Fuel | Piper 39995-034 | Inlet fuel hose to engine fuel pump. |
The FAA is correcting an airworthiness directive (AD) that published in the Federal Register. That AD applies to certain Piper Aircraft, Inc. Model PA-31-350 airplanes. The wing locations of engine TIO-540-J2B and LTIO-540-J2B in table 1 of the Applicability, paragraph (c), section are incorrect. This document corrects that error. In all other respects, the original document remains the same; however we are publishing the entire rule in the Federal Register.
(1) Within the next 60 hours time-in-service (TIS) after June 6, 2016 (the effective date of this AD) or within the next 6 months after June 6, 2016 (the effective date of this AD), whichever occurs first, inspect to determine the clearance between the inlet and exit fuel hose assemblies listed in table 1 to paragraph (c) of this AD, and each turbocharger support assembly, Lycoming P/N LW-18302. There should be a minimum 3/16-inch clearance. Do the inspection following the INSTRUCTIONS section of Piper Aircraft, Inc. Service Bulletin No. 1257A, dated August 4, 2015.
(2) Before further flight after the inspection required in paragraph (g)(1) of this AD, if the measured clearance is less than 3/16-inch, make all necessary adjustments to make the clearance a minimum of 3/16-inch between the inlet and exit fuel hose assemblies listed in table 1 to paragraph (c) of this AD and each turbocharger support assembly, Lycoming P/N LW-18302, following the INSTRUCTIONS section of Piper Aircraft, Inc. Service Bulletin No. 1257A, dated August 4, 2015.
(1) Within the next 60 hours TIS after June 6, 2016 (the effective date of this AD) or within the next 6 months after June 6, 2016 (the effective date of this AD), whichever occurs first, visually inspect the inlet and exit fuel hose assemblies listed in table 1 to paragraph (c) of this AD for evidence of leaking, cracking, chafing, and any other sign of damage. Do the inspection following the INSTRUCTIONS section of Piper Aircraft, Inc. Service Bulletin No. 1257A, dated August 4, 2015.
(2) Before further flight after the inspection required in paragraph (h)(1) of this AD, if any evidence of leaking, cracking, chafing, or any other sign of damage is found in any inlet or exit fuel host assembly listed in table 1 to paragraph (c) of this AD, replace the fuel hose assembly with a serviceable part. Do the replacement following the INSTRUCTIONS section of Piper Aircraft, Inc. Service Bulletin No. 1257A, dated August 4, 2015.
(1) Within the next 60 hours TIS after June 6, 2016 (the effective date of this AD) or within the next 6 months after June 6, 2016 (the effective date of this AD), whichever occurs first, visually inspect each turbocharger support assembly, Lycoming P/N LW-18302, for evidence of chafing and any other signs of damage. Do the inspection following the INSTRUCTIONS section of Piper Aircraft, Inc. Service Bulletin No. 1257A, dated August 4, 2015.
(2) Before further flight after the inspection required in paragraph (i)(1) of this AD, if any evidence of chafing or any other sign of damage is found on any turbocharger support assembly, replace Lycoming P/N LW-18302 with a serviceable part. Do the replacement following the INSTRUCTIONS section of Piper Aircraft, Inc. Service Bulletin No. 1257A, dated August 4, 2015.
(1) If any fuel line component was adjusted or replaced during any actions required in paragraphs (g)(1) through (i)(2) of this AD, before further flight, perform an engine run-up on the ground to check for leaks. Do the engine run-up following the INSTRUCTIONS section of Piper Aircraft, Inc. Service Bulletin No. 1257A, dated August 4, 2015.
(2) If any leaks found during the engine run-up required in paragraph (j)(1) of this AD emanate from any fuel line component adjusted, repaired, or replaced during any actions required in paragraphs (g)(1) through (i)(2) of this AD, before further flight, take all necessary corrective actions following the INSTRUCTIONS section of Piper Aircraft, Inc. Service Bulletin No. 1257A, dated August 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.
