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57-22-01: 57-22-01 PIPER: Applies to All Models PA-16, PA-20 and PA-22 Aircraft.
Compliance required as indicated.
To preclude the possibility of inflight fires the following inspection and rework is necessary to eliminate combustible material and possible ignition sources from the area aft of the firewall, underneath the forward cabin floor. Access to this section may be gained by removing the metal panels or opening the fuselage side cowl panels rearward of the firewall underneath the aircraft as shown in Piper Service Bulletin No. 161a. The relative difficulty in gaining access to this area has probably contributed to poor maintenance.
1. On all PA-16, PA-20, and PA-22 aircraft, Serial Numbers 22-1 through 22-2699, the following inspection and rework is necessary prior to December 15, 1957. Remove and discard any sound-proofing material contaminated with engine or hydraulic oil. Where the plastic septum has separated from the fiberglass or shows signs of drying or cracking it should be removed in its entirety from the affected blanket. Uncontaminated fiberglass, from which the plastic septum has been removed, may be continued in service. Inspect electrical wiring for chafing of the insulation and replace any found in an unsatisfactory condition. Check for a reasonable clearance between hydraulic lines, electrical wires, control cables and fuel lines and rework as necessary. The sealing of the firewall on all affected aircraft must be inspected as described in Piper Service Bulletin No. 161a and when found deficient must be resealed in accordance with the manufacturer's service bulletin or accepted aeronautical practices.
2. On PA-22 aircraft Serial Numbers 22-2700 to 22-6194 inclusive, the procedure outlined in 1 should be followed within the next 100 hours of operation.
3. Periodic inspection should be made of the exhaust system in accordance with Piper Service Bulletin No. 161a pertaining to inspection of the exhaust stack gaskets,exhaust stacks, muffler assembly, and muffler tailpipe.
4. The sealing of the firewall on all PA-16, PA-20 and PA-22 aircraft must be inspected at 100-hour intervals in accordance with Piper Service Bulletin No. 161a. If found deficient, it must be resealed in accordance with the manufacturer's service bulletin or accepted aeronautical practices.
5. The 100-hour inspection requirement on all Model Piper PA-22 aircraft, Serial Numbers 22-1 to 22-6194 inclusive, can be eliminated if Piper Kit, P/N 754237 or equivalent, is installed.
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59-12-09: 59-12-09 PIPER: Applies to PA-24 and PA-24 "250" Aircraft Serial Numbers 24-1 Through 24-764, 24-766 Through 24-779, 24-781 Through 24-820, 24-822 Through 24-842, 24- 844 Through 24-849, 24-851 Through 24-856, 24-858, 24-860 Through 24-865, 24-867 Through 24-871, 24-875, 24-878, 24-880, 24-881, and 24-885.
Compliance required not later than July 30, 1959.
Due to a recent inflight incident where control wheel sprocket stud P/N 20913-00 failed, inspect the sprocket stud P/N 20913-00 where the sprocket was attached on all aircraft that have or have had an automatic control system installed and ascertain that the stud is not cracked or twisted and the hole is not elongated. Parts found cracked or damaged are to be replaced before further operation.
(Piper Service Bulletin No. 172 covers this inspection in detail.)
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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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