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2008-16-08: We are adopting a new airworthiness directive (AD) for the products listed above. This AD results from 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:
During approach, a Falcon 2000EX operator experienced a temporary loss of the 4 Electronic Flight Instrumentation System (EFIS) display units followed by a consecutive restart of the avionics. During initial investigation, a loose connection on the DC load distribution system was discovered and determined to be the root cause of this event. However, further analysis pointed out that large electrical transients on the essential bus bar may possibly cause simultaneous and temporary power shortage on both sides of the electrical system.
This Airworthiness Directive (AD) * * * action is necessary to prevent a momentary loss of data on the EFIS screens, which could lead to the pilot's loss of situational awareness during initial climb or approach/landing, and possibly result in reduced control of the airplane. * * *
We are issuing this AD to require actions to correct the unsafe condition on these products.
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59-08-03: 59-08-03 PIPER: Applies to Model PA-23, Serial Numbers 23-1502 To 23-1558 Inclusive, 23-1560 To 23-1562 Inclusive and 23-1565 To 23-1567 Inclusive.
Compliance required by May 1, 1959.
Install an operating limitations placard on the instrument panel stating "This airplane must be operated as a normal category airplane in compliance with the airplane flight manual. Acrobatic maneuvers including spins prohibited."
(Piper Service Bulletin No. 169 covers this subject.)
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59-06-05: 59-06-05 PIPER: Applies to Models PA-24 and PA-24 "250", Serial Numbers 24-1 To 24-503 Inclusive.
Compliance required by June 1, 1959.
Due to failures of the nose gear elastic bungee cord, P/N 31322-08, it must be replaced by a coil spring and link arrangement, Piper Modification Kit P/N 754 205 or equivalent.
(Piper Service Bulletin No. 168 covers this subject.)
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58-25-05: 58-25-05 PIPER: Applies to Model PA-24 Aircraft, Serial Numbers 1 Through 336.
Compliance required by February 1, 1959.
It has been determined that an unsafe condition exists with respect to the door latch arrangement of the aircraft affected. At present it is not possible to open the cabin door from the inside if it has been locked on the outside. In order to preclude occupants becoming inadvertently locked inside the cabin of PA-24 aircraft in the case of some emergency, the main cabin door latch assembly must be modified to permit opening the door from inside the aircraft under all conditions.
(Item No. 1 of Piper Service Letter No. 305 dated October 1, 1958, presents an acceptable method of modifying the aircraft.)
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58-12-02: 58-12-02 PIPER: Applies to All Models J-3, PA-11, PA-15, PA-16 and PA-17 Aircraft.
Compliance required not later than July 15, 1958.
There is a possibility that some aileron hinge reinforcing brackets P/N 10931-02 supplied to the field during the past three years were fabricated from aluminum instead of steel. Brackets, which have been replaced since June 1954, must be inspected to determine the type of material. All aluminum brackets are to be removed and replaced with steel brackets.
(Piper Service Bulletin No. 165 covers this subject.)
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58-04-03: 58-04-03 PIPER: Applies to Model PA-23 Aircraft, Serial Numbers 23-1 to 2-1253 Inclusive.
Compliance required at next 100-hour inspection but not later than April 1, 1958, whichever occurs first.
As a result of a number of failures, the hollow rudder trim tab adjustment screw, P/N 18453-00, must be replaced with a solid screw, P/N 18453-02.
(Piper Service Bulletin No. 162 covers this same subject.)
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2008-15-04: We are adopting a new airworthiness directive (AD) for BHTC Model 430 helicopters. This AD results from 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 aviation authority of Canada, with which we have a bilateral agreement, states in the MCAI: "It has been determined that the existing rigging procedures for the tail rotor pitch change mechanism have to be changed due to possibility of parts interference.'' The cumulative effect of individual part tolerances resulting in the total assemblage of those parts being out of tolerance could result in the tail rotor yoke striking another part other than the flapping stop (parts interference) cited in the MCAI. Also, the misalignment of the tail rotor counterweight bellcrank may result in higher tail rotor pedal forces and a higher pilot workload after failure of the 1 hydraulic system. Both parts interference and the misaligned counterweight bellcrank create an unsafe condition. This AD require actions that are intended to address these unsafe conditions.
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57-21-01: 57-21-01 PIPER: Applies to All Model PA-23 Aircraft.
Compliance required at next regular inspection period but not to exceed 100 hours.
Inspect the attachment of the rudder trim tab control rod to the rudder trim tab. If a flat head pin has been installed it must be replaced by an AN 23-10 clevis bolt and AN 960-10L washer, secured with an AN 320-3 nut and AN 380-2-2 cotter pin.
(Piper Service Bulletin No. 159 covers this subject.)
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2008-15-05: We are adopting a new airworthiness directive (AD) for all Boeing Model 737-300, -400, and -500 series airplanes. This AD requires inspecting to determine if certain carriage spindles are installed, repetitive inspections for corrosion and indications of corrosion on affected carriage spindles, and if necessary, related investigative action and corrective action. This AD also provides optional terminating action. This AD results from a report of corrosion found on carriage spindles that are located on the outboard trailing edge flaps. We are issuing this AD to detect and correct corrosion of the carriage spindle, which could result in fracture. Fracture of both the inboard and outboard carriage spindles, in the forward ends through the large diameters, on a flap, could adversely affect the airplane's continued safe flight and landing.
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57-19-01: 57-19-01 PIPER: Applies to Model PA-23, Serial Numbers 23-129, 23-132 to 23-228 Inclusive; 23-230 to 23-766 Inclusive; 23-768 to 23-850 Inclusive; 23-852 to 23-883 Inclusive; 23-885 to 23-937 Inclusive; 23-939 to 23-1017 Inclusive; 23-1019, 23-1020, 23-1022 to 23-1030 Inclusive; 23-1032 to 23-1042 Inclusive; 23-1044, 23-1046 to 23-1057 Inclusive; 23-1059 to 23- 1064 Inclusive; 23-1066, 23-1069 to 23-1074 Inclusive; 23-1076, 23-1078 to 23-1082 Inclusive.
Compliance required by November 1, 1957.
Inspect the Heim rod end bearing (P/N HMX-4M) located where the front elevator control tube attaches to the lower horn on the control column. If more than six threads show on the rod end, rerig the control column so that six or less threads are exposed.
(Piper Service Bulletin No. 156 dated July 2, 1957, covers this subject.)
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