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Airworthiness directives › 2013-05-14

AD 2013-05-14 Airworthiness Directives; Bell Helicopter Textron, Inc.

2013-04-26
2013-03-22
39-17386
FAA-2012-1016
Airframe
—

Applicability*9

This AD becomes effective April 26, 2013.

Compliance

No special flight permits will be issued for any helicopter installed with outer ring, P/N 412-010-407-105, if the outer ring has 2,500 hours or more TIS.

Required actions

(1) The Manager, Safety Management Group, FAA, may approve AMOCs for this AD. Send your proposal to: Michael Kohner, Aviation Safety Engineer, Rotorcraft Certification Office, Rotorcraft Directorate, FAA, 2601 Meacham Blvd., Fort Worth, TX 76137; telephone (817) 222-5447; email 7-avs-asw-170@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

(1) Within 30 days, establish a retirement life of 2,500 hours time-in-service (TIS) for any affected outer ring on the component history card or equivalent record. Revise the helicopter Airworthiness Limitations section of the applicable maintenance manual or Instructions for Continued Airworthiness (ICA) by establishing the new retirement life by making pen-and-ink changes or inserting a copy of this AD into the maintenance manual or the ICAs. (2) For any affected outer ring that, on the effective date of this AD, has 2,200 or more hours TIS, within 300 hours TIS, replace the outer ring with an airworthy outer ring. (3) Within 12 months, for any affected outer ring, regardless of the number of hours TIS, replace the outer ring with an airworthy outer ring. (4) Do not install outer ring, P/N 412-010-407-105, on any helicopter.

Affected ADs

This AD defines the unsafe condition as cracking in the outer ring, which could result in the loss of main rotor (M/R) blade pitch control and subsequent 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