Airworthiness directives › 2021-18-01
AD 2021-18-01 Airworthiness Directives; B-N Group Ltd. Airplanes
Models named: BN-2, BN-2A, BN-2A-2, BN-2A-3, BN-2A-6, BN-2A-8, BN-2A-9, BN-2A-20, BN-2A-21, BN-2A-26. Read the applicability below — it usually turns on serial or part numbers too.
Applicability*9
This AD applies to B-N Group Ltd. Models BN-2, BN-2A, BN-2A-2, BN-2A-3, BN-2A-6, BN-2A-8, BN-2A-9, BN-2A-20, BN-2A-21, BN-2A-26, BN-2A-27, BN-2B-20, BN-2B-21, BN-2B-26, BN-2B-27, BN-2T, and BN-2T-4R airplanes, all serial numbers, certificated in any category, with a rudder final drive rod part number (P/N) NB-45-0991 installed.
Compliance
Comply with this AD within the compliance times specified, unless already done.
Required actions
(1) Inspect the rudder final drive rod assembly for loose taper pins, loose end connections, bending, and cracks within the applicable compliance times for your airplane specified in paragraph (g)(1)(i) or (ii) of this AD. (i) For Models BN-2, BN-2A, BN-2A-2, BN-2A-3, BN-2A-6, BN-2A-8, BN-2A-9, BN-2A-20, BN-2A-21, BN-2A-26, BN-2A-27, BN-2B-20, BN-2B-21, BN-2B-26, and BN-2B-27 airplanes, within 100 hours time-in-service (TIS) after the effective date of this AD and thereafter at intervals not to exceed 1,000 hours TIS. (ii) For Models BN-2T and BN-2T-4R airplanes, within 200 hours TIS after the effective date of this AD and thereafter at intervals not to exceed 1,000 hours TIS. (2) If a loose taper pin, a loose end connection, any bending, or a crack is found during any inspection required by paragraph (g)(1) of this AD, before further flight, replace the rudder final drive rod assembly by following section 7, Removal and Installation Instructions for Unserviceable Units, of Britten-Norman Service Bulletin Number SB 363, Issue 3, dated May 23, 2018 (SB 363, Issue 3) or Britten-Norman Service Bulletin Number SB 364, Issue 3, dated May 23, 2018 (SB 364, Issue 3), as applicable to your model airplane. (3) If no loose taper pins, no loose end connections, no bending, and no cracks are found during the initial inspection required by paragraph (g)(1) of this AD, review the airplane maintenance records to determine whether any taper pins have been replaced or reworked on the rudder final drive rod assembly. If a taper pin has ever been replaced or reworked, without exceeding the initial compliance time in paragraph (g)(1)(i) or (ii) of this AD, replace the rudder final drive rod assembly by following section 7, Removal and Installation Instructions for Unserviceable Units, of SB 363, Issue 3 or SB 364, Issue 3, as applicable to your model airplane. (4) As of the effective date of this AD, do not install a rudder final drive rod assembly P/N NB-45-0991 on any airplane unless: (i) The rudder final drive rod assembly is unused (zero hours TIS); or (ii) The taper pins in the rudder final drive rod assembly have never been replaced. (5) As of the effective date of this AD, do not replace any taper pin on a rudder final drive rod assembly P/N NB-45-0991 installed on any airplane.
Unsafe condition
This AD was prompted by mandatory continuing airworthiness information (MCAI) originated by an aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as failure of the rudder final drive rod because of cracks in the region of the taper pins. The FAA is issuing this AD to detect and correct defects on the rudder final drive rod assembly to prevent failure of the assembly. The unsafe condition, if not addressed, could result in loss of rudder control and reduced airplane control.
Affected ADs
None.
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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