Airworthiness directives › 2018-01-12
AD 2018-01-12 Airworthiness Directives; Airbus Helicopters
Applicability*9
This AD replaces AD 2018-01-12, Amendment 39-19153 (83 FR 2039, January 16, 2018).
Compliance
(1) Before further flight, insert a copy of this AD into the rotorcraft flight manual, Section 4 Normal Operating Procedures, or make pen and ink changes to the preflight and post-flight procedures as follows: (i) Stop performing the yaw load compensator check (ACCU TST switch) during preflight procedures, and instead perform the yaw load compensator check during post-flight procedures after rotor shut-down. (ii) The yaw servo hydraulic switch (collective switch) must be in the “ON” (forward) position before takeoff. Note 2 to paragraph (f)(1)(ii) of this AD: The yaw servo hydraulic switch is also called the hydraulic pressure switch or hydraulic cut off switch in various Airbus Helicopters rotorcraft flight manuals. (2) Within 350 hours time-in-service: (i) Install a timer relay for the yaw servo hydraulic switch (collective switch) by following the Accomplishment Instructions, paragraph 3.B.2.b.1, 3.B.2.b.2, 3.B.2.b.3, 3.B.2.b.4, 3.B.2.b.5, or 3.B.2.b.6, as applicable to the configuration of your helicopter, of Airbus Helicopters Service Bulletin (SB) No. AS350-67.00.64, Revision 0, dated February 25, 2015 (AS350-67.00.64). If your helicopter has an automatic pilot system, also comply with paragraph 3.B.2.b.7 of AS350-67.00.64. (ii) Install an indicator light on the caution and warning panel by following the Accomplishment Instructions, paragraph 3.B.2.c.1 or 3.B.2.c.2, as applicable to the configuration of your helicopter, of AS350-67.00.64. (iii) For helicopters with a Geneva Aviation P122 or P132 electrical console installed, replace the ESN-11 HYD TEST (ACCU TST) switch with a monostable toggle switch part number MS24658-26F. (iv) For helicopters without a Geneva Aviation P122 or P132 electrical console installed, replace the bistable ACCU TST button on the control panel with a monostable button as depicted in Figure 1 or Figure 3, as applicable to the configuration of your helicopter, of Airbus Helicopters SB No. AS350-67.00.65, Revision 0, dated August 25, 2016. (3) After the effective date of this AD, do not install a bistable ACCU TST button on any helicopter.
Required actions
A special flight permit may be issued for paragraph (f)(2) of this AD only.
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 lack of hydraulic pressure in a tail rotor (T/R) hydraulic system. This condition could result in loss of T/R flight control and subsequent loss of control of the helicopter.
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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