Airworthiness directives › 2013-03-16
AD 2013-03-16 Airworthiness Directives; Bell Helicopter Textron Helicopters
Applicability*9
This AD supersedes AD 2011-08-01, Docket No. FAA-2011-0323, Amendment 39-16651 (76 FR 18865, April 6, 2011), Directorate Identifier 2011-SW-005-AD.
Compliance
(1) Within 25 hours time-in-service or 15 days, whichever occurs first, perform a magnetic particle inspection (MPI) of each fitting for a crack. If an MPI was already performed on a fitting resulting in re-identifying the fitting with “FM” at the end of the P/N or at the end of the P/N on the fitting's component history card or equivalent record, then the requirements of this AD have been met. (2) If a fitting is cracked, before further flight, replace it with an airworthy fitting. (3) If a fitting is not cracked, before further flight, re-identify the fitting by adding “FM” at the end of the P/N using a vibrating stylus. The depth of the “FM” must not exceed 0.005 inches or extend within 0.10 inch of the part's edge. Also, add “FM” at the end of the P/N on the fitting's component history card or equivalent record.
Required actions
(1) The Manager, Rotorcraft Certification Office, FAA, may approve AMOCs for this AD. Send your proposal to: Michael Kohner, Aerospace Engineer, FAA, Rotorcraft Directorate, Rotorcraft Certification Office, 2601 Meacham Blvd., Fort Worth, Texas, 76137, phone: (817) 222-5170; fax: (817) 222-5783; email: mike.kohner@faa.gov. (2) For operations conducted under a 14 CFR part 119 operating certificate or under 14 CFR part 91, subpart K, we suggest that you notify your principal inspector, or lacking a principal inspector, the manager of the local flight standards district office or certificate holding district office, before operating any aircraft complying with this AD through an AMOC.
Unsafe condition
You are responsible for performing each action required by this AD within the specified compliance time unless it has already been accomplished prior to that time.
Affected ADs
This AD defines the unsafe condition as a crack in the fitting and the determination that additional part-numbered fittings may not have been manufactured in accordance with approved manufacturing processes and controls. This condition could result in failure of a fitting, loss of a main rotor blade, and loss of helicopter control.
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The directive text above is reproduced from the Federal Register, a work of the United States government and in the public domain. The separation into applicability, compliance and required actions is TrackAD's.*1