Results
74-21-02: 74-21-02 PIPER: Amendment 39-1981. Applies to Piper PA-36-285 airplanes serial numbers 36-7360001 through 36-7460025 certificated in all categories. Compliance required within the next 50 hours time in service after the effective date of this AD, unless already accomplished. To provide a more reliable stall warning system, accomplish the lift detector relocation and modification per Piper Service Bulletin No. 418 or equivalent approved by the Chief, Engineering and Manufacturing Branch, Federal Aviation Administration, Southern Region. This amendment becomes effective October 4, 1974.
74-19-01: 74-19-01 PIPER: Amendment 39-1952. Applies to Piper PA-28-235 airplanes, serial numbers 28-7410001 through 28-7410090, PA-32-260 airplanes serial numbers 32-7400001 through 32-7400047, PA-32-300 airplanes 32-7440001 through 32-7440147, and PA-34-200 airplanes serial numbers 34-7450001 through 34-7450205 certificated in all categories. Compliance required within the next ten hours time in service after the effective date of this AD, unless already accomplished. To detect improperly formed lightening holes in the outer wing spars, accomplish the following: (a) PA-28-235 and PA-32 series airplanes (1) Remove the inspection plate on bottom of wing which is located adjacent to the aileron bellcrank. (2) Inspect both sides of left and right spar around the first lightening hole outboard of the fish mouth of the main spar splice for evidence of a die stamping mark approximately six by six inches square surrounding the lightening hole area. (3) Inspect the lightening hole flange radius for cracks. (b) PA-34 series airplanes (1) Remove the inspection plate on bottom of wing which is located adjacent to the aileron bellcrank and aft of the outboard fuel tank. (2) Inspect as in paragraph (a)(2) around first and second lightening holes outboard of the fish mouth at the main spar splice. (3) Inspect the lightening flange radii for cracks. (c) If square die stamping mark is evident on the aft side of spar only and there are no cracks in the lightening hole flange radii, no further action is required. (d) If square die stamping mark is evident on forward side of spar and/or if there are cracks in the lightening hole flange, replace the outboard spar with a serviceable spar of the same part number or repair in a method approved by the Chief, Engineering and Manufacturing Branch, FAA Southern Region. (e) Report positive findings from paragraph (d) to Chief, Engineering and Manufacturing Branch, FAA SouthernRegion within 10 days of inspection. (Reporting approved by the Bureau of the Budget under BOB No. 04-R0174.) This amendment becomes effective September 7, 1974.
74-18-06: 74-18-06 PIPER: Amendment 39-1932. Applies to PA-28-235 airplanes Serial numbers 28-7310001 to 28-7310064 inclusive and 28-7410001 to 28-7410039 inclusive certificated in all categories. Compliance required within the next 50 hours' time in service after the effective date of this AD, unless already accomplished. To detect and replace erroneous fuel quantity placards, accomplish the following: 1. Inspect the fuel quantity placards located on both aircraft wing (inboard main) fuel tanks and replace each placard that does not state "Usable fuel capacity 24 gallons", with Placard Piper Part Number 69669-64V or an equivalent placard approved by the Chief, Engineering and Manufacturing Branch, Federal Aviation Administration, Southern Region. 2. Inspect the fuel selector placard (in the aircraft cabin) and replace the placard if it does not state "24 gallons" at both the left main and the right main positions with Placard Piper Part Number 69672-00V or an equivalent placard approved by the Chief, Engineering and Manufacturing Branch, Federal Aviation Administration, Southern Region. Piper Service Letter No. 720 pertains to this same subject. This amendment becomes effective August 28, 1974.
2007-12-20: We are adopting a new airworthiness directive (AD) for the products listed above. This AD results from mandatory continuing airworthiness information (MCAI) issued by an airworthiness authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as electrical arcing due to chafing between a bonding cable and electrical wires in the 120 VU (volt unit) electrical harness, causing the loss of some instruments and loss of one hydraulic circuit pressure (i.e., loss of pressure of one hydraulic circuit). We are issuing this AD to require actions to correct the unsafe condition on these products.
2001-02-05: This amendment supersedes an existing airworthiness directive (AD), applicable to Model CL-604 variant of Bombardier Model Canadair CL-600-2B16 series airplanes modified in accordance with certain Supplemental Type Certificates, that currently requires that the fuel service panel maintenance light on the fuel service panel be disconnected. This amendment requires modification of the wiring of the fuel port flood light (which is the name given to the fuel service panel maintenance light in the service bulletin that describes the wiring modification). This amendment is prompted by a report indicating that an electrical spark was noted when the fuel cap chain contacted the fuel port flood light housing of the fuel service panel. The actions specified by this AD are intended to prevent electrical sparks from a grounded object from coming into contact with the fuel port flood light housing of the fuel service panel, which could result in a fuel fire due to the proximity of thefuel service panel to the fuel port.
2018-03-14: We are adopting a new airworthiness directive (AD) for Pacific Aerospace Limited Model 750XL airplanes. This AD results from mandatory continuing airworthiness information (MCAI) issued by the aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as non-conforming fuel tank caps, which could lead to fuel loss during flight. We are issuing this AD to require actions to address the unsafe condition on these products.
74-14-04: 74-14-04 PIPER: Amendment 39-1886 as amended by Amendment 39-1916. Applies to Piper PA-28-151 airplanes serial numbers 28-7415001 through 28-7415530, 28-7415532 through 28-7415534, and 28-7415537 through 28-7415538, certificated in all categories. Compliance required as indicated. To insure required positive margin of safety, accomplish the following: (a) Effective immediately and until further notice by airworthiness directive, flight operations shall be conducted at 2150 pounds or less for normal category operation and 1825 pounds or less for utility category operations. (b) Within ten hours time in service after receipt of this airmail letter, install a placard on the instrument panel in full view of the pilot with the following wording: "NORMAL CATEGORY MAXIMUM GROSS WEIGHT - 2150 POUNDS, UTILITY CATEGORY MAXIMUM WEIGHT - 1825 POUNDS. THIS PLACARD INSTALLED PER FAA AIRWORTHINESS DIRECTIVE ISSUED JUNE 12, 1974." The letters on the above placard shouldbe at least one eighth inch in height and on a suitable material which can be expected to remain affixed in position and resist deterioration. (c) The maximum weights specified in the limitation section of the PA-28-151 airplane flight manual must be changed by appropriate entry from 2325 pounds to 2150 pounds for normal category and from 1950 pounds to 1825 pounds for utility category. Note: The forward center of gravity limit in normal category operation becomes 85.1 inches aft of datum. (d) After installation of Piper Kit 760878V in accordance with Piper Service Bulletin Number 424 or equivalent modification approved by the Chief, Engineering and Manufacturing Branch, FAA, Southern Region, the airplane may be operated up to 2325 pounds gross weight in the normal category and up to 1950 pounds gross weight in the utility category. After modification the placard as called for in paragraph (b) is to be removed and the limitation section of the PA-28-151 Airplane Flight Manual must reflect maximum weights of 2325 and 1950 for normal and utility categories respectively. Amendment 39-1886 was effective July 8, 1974 and was effective upon receipt for all recipients of the airmail letters dated June 12, 1974 and June 19, 1974 which contained this amendment. This Amendment 39-1916 becomes effective August 14, 1974.
74-13-04: 74-13-04 PIPER: Amendment 39-1875. Applies to PA-28-140 airplanes Serial Numbers 28-25001 to 28-26331 inclusive; 28-26401 to 28-26946 inclusive; 28-7125001 to 28-7125641 inclusive, and 28-7225001 to 28-7425354 inclusive. Compliance required within the next 50 hours time in service after the effective date of this AD, unless already accomplished. To prevent the loss of power due to a failed ball joint assembly, accomplish the following: (a) Remove the lower engine cowl. (b) Remove the throttle control cable ball joint assembly (P/N 31747-00) from throttle control cable and carburetor throttle lever or alignment bracket if installed. (c) Accomplish the following in accordance with instructions in Piper Kit 760 780V or an equivalent procedure approved by Chief, Engineering and Manufacturing Branch, Federal Aviation Administration, Southern Region: (1) Install Alignment Bracket (Piper Part Number 99929-0) unless already installed to the carburetor throttle lever using two each AN3-5A Machine Bolts, AN960-10 Flat Washers and MS20365-1032C Nuts. (2) Install spherical rod end bearing (Piper Part Number 452-557) to throttle control cable and the 99929-0 Alignment Bracket using one AN3-10 Machine Bolt, one Piper Part Number 62833-101 Washer, one AN310-3 Nut, one MS24665-132 Cotter Pin and two Piper Part Number 63900-78 Spacers. (3) Adjust so that the throttle closes completely and has some cushion at the throttle control handle in the cockpit. (4) Check the inspection hole for visible threads and tighten the jam nut against the rod end. (d) Replace the lower engine cowl. Piper Service Letter No. 670 or other approved later revision pertains to this same subject. This amendment becomes effective June 21, 1974.
2007-12-07: The FAA is adopting a new airworthiness directive (AD) for GE CF6-80C2B series turbofan engines with electronic control units (ECUs), installed on Boeing 747 and 767 series airplanes. This AD requires installing software version 8.2.Q1 to the engine ECU, which increases the engine's margin to flameout. This AD results from reports of engine flameout events during flight, including reports of events where all engines simultaneously experienced a flameout or other adverse operation. Though the root cause investigation is not yet complete, we believe exposure to ice crystals during flight is associated with these flameout events. We are issuing this AD to provide increased margin to flameout, which will minimize the potential of an all-engine flameout event caused by ice accretion and shedding during flight.
2018-03-17: We are adopting a new airworthiness directive (AD) for Aeroclubul Romaniei Model IS-28B2 gliders. This AD results from mandatory continuing airworthiness information (MCAI) issued 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 cracks at stringers in the rear fuselage of several Model IS-28B2 gliders. We are issuing this AD to require actions to address the unsafe condition on these products.