Results
2019-14-02: The FAA is adopting a new airworthiness directive (AD) for all The Boeing Company Model 737 series airplanes. This AD was prompted by a \n\n\nreport that structural fatigue cracks can develop in certain aluminum pressure module check valves prior to the design limit. This AD requires an inspection to determine the part numbers of the four hydraulic systems A and B pressure module check valves and applicable on-condition actions. The FAA is issuing this AD to address the unsafe condition on these products.
2001-02-51: This document publishes in the Federal Register an amendment adopting airworthiness directive (AD) 2001-02-51 that was sent previously to all known U.S. owners and operators of EMBRAER Model EMB-145 and EMB-135 series airplanes by individual notices. This AD requires revising the FAA-approved airplane flight manual and installing placards to alert the flight crew to the maximum speed for airplane retrimming after takeoff and during the climb phase. This action is prompted by issuance of mandatory continuing airworthiness information by a foreign airworthiness authority. The actions specified by this AD are intended to prevent high pitch control forces, which could result in possible loss of control of the airplane.
2019-13-04: The FAA is adopting a new airworthiness directive (AD) for certain ATR-GIE Avions de Transport R(eacute)gional Model ATR72 airplanes. This AD was prompted by a determination that new or more restrictive maintenance instructions and airworthiness limitations are necessary. This AD requires revising the existing maintenance or inspection program, as applicable, to incorporate new or more restrictive maintenance instructions and airworthiness limitations. The FAA is issuing this AD to address the unsafe condition on these products.
75-06-04: 75-06-04 PIPER: Amendment 39-2121. Applies to Model PA-31-350, Serial Nos. 31- 5001 through 31-7405495 certificated in all categories. Compliance required within the next ten hours in service from the effective date of this AD unless previously accomplished, as indicated. 1. Inspect the forward rudder control cable installation as follows: a. Remove the left pilot's seat and associated floor panels. b. Inspect the left- and right-hand forward rudder control cables P/N 41947-03 for proper routing between the pulleys and cable guard pins. c. Remove the forward rudder cable guard pins and inspect the pins for evidence of contact with the control cable. d. If a forward rudder control cable is not properly routed or the cable guard pins show evidence of contact with the control cable, the control cable must be replaced with an acceptable part of the same part number, before further flight, except that the airplane may be flown in accordance with FAR 21.197 to a base where repairs can be made. (Piper Service Bulletin No. 379A refers to this subject.) This amendment is effective March 13, 1975, and was effective for all recipients of the airmail dispatch of February 12, 1975, upon receipt.
2000-23-52: This document publishes in the Federal Register an amendment adopting superseding Airworthiness Directive (AD) 2000-23-52, which was sent previously to all known U.S. owners and operators of Sikorsky Aircraft Corporation (Sikorsky) Model S-76A, S-76B, and S-76C helicopters by individual letters. This AD requires, before further flight, performing a fluorescent penetrant inspection of the main rotor shaft assembly (shaft). Also required are recurring fluorescent penetrant inspections and visual inspections for any crack. If any crack is found, the shaft must be replaced with an airworthy shaft before further flight. This amendment is prompted by the discovery of two in-service cracked shafts, one with 477 hours time-in-service (TIS) and one with 313 hours TIS. A third shaft, that had been rejected from the manufacturing process for other reasons, was also discovered to have a crack. The actions specified by this AD are intended to prevent failure of the shaft and subsequent loss of control of the helicopter.
2007-12-23: This amendment adopts a new airworthiness directive (AD) for MD Helicopters, Inc. (MDHI) Model 369A, 369D, 369E, 369F, 369FF, 369H, 369HE, 369HS, 369HM, 500N, and OH-6A helicopters that requires inspecting each landing gear fairing support assembly (support assembly), replacing or reworking certain forward and aft landing gear assemblies, and creating an access hole to facilitate inspections and a recurring inspection. A terminating action for the requirements of this AD is also provided. This amendment is prompted by five reports of landing gear strut (strut) failures. The actions specified by this AD are intended to detect a crack that could result in the failure of a strut and subsequent loss of control of the helicopter during landing.
2007-12-19: 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 explosion risks. Chafing of the fuel pump cables could result in short circuits leading to fuel pump failure, intermittent operation, arcing, and possible fuel tank explosion. We are issuing this AD to require actions to correct the unsafe condition on these products.
74-26-07: 74-26-07 PIPER: Amendment 39-2047. Applies to Model PA-28-180 airplanes serial numbers 28-7305001 through 28-7505079 certificated in all categories. Compliance required as indicated. To detect an incorrect placard accomplish the following: a. Before further flight, unless already accomplished, check the airplane Operating Limitations Placard to insure that it indicates that spins are not approved for normal and utility category operation. If placard correctly indicates that spins are not approved, no further action is necessary. b. If the incorrect placard is installed, cut out appropriate temporary Operating Limitations Placard from Piper Service Bulletin No. 436 or an FAA approved equivalent and attach over existing placard before further flight. c. If a temporary placard is necessary, install permanent placard Piper Part No. 76206-00 (m.p.h.) or 76298-00 (knots) or an FAA approved equivalent within 100 hours time in service from the effective date of this AD. The action required by paragraphs (a) and (b) may be performed by the pilot. Note: For the requirements regarding the listing of compliance and method of compliance with this AD in the airplanes permanent maintenance record, see FAR 91.173. This amendment becomes effective December 21, 1974.
2018-03-16: We are superseding Airworthiness Directive (AD) 2017-10-11 for Stemme AG Model Stemme S10-VT gliders (type certificate previously held by Stemme GmbH & Co. KG). This AD results from mandatory continuing airworthiness information (MCAI) issued by an aviation authority of another country to identify and address an unsafe condition on an aviation product. The MCAI describes the unsafe condition as certain propeller front transmission gear wheels having insufficient material strength because of improper heat treatment during manufacturing. We are issuing this AD to require actions to address the unsafe condition on these products and to add Stemme AG Model Stemme S 12 gliders to the Applicability section.
2001-02-12: This amendment adopts a new airworthiness directive (AD) that is applicable to CFMI model CFM56-7B turbofan engines. This action requires a one-time on-wing torque inspection, and torque if needed, of all the PS3 pressure line fittings to insure proper torque. This amendment is prompted by service events which resulted in two in-flight shutdowns (IFSD's) and an aborted takeoff due to the disconnection of one of the PS3 line fittings. The actions specified in this AD are intended to prevent air leakage from incorrectly torqued fittings of the PS3 line, which could result in engine power loss.
74-26-10: 74-26-10 PIPER AIRCRAFT: Amendment 39-2053. Applies to Magneto Switch Guard Installation on Piper PA-31 and PA-31-300 S/N 31-2 to 31-7300969 incl; PA-31-350 S/N 31- 5001 to 31-7305091 incl; and PA-31P S/N 31P-1 to 31P-7300161 incl. To prevent inadvertently or accidentally shutting down an engine, perform the following: 1. Within the next 100 hours time in service, after the effective date of this Airworthiness Directive, install a protective guard over the magneto switches in accordance with Piper Service Letter No. 675, dated September 17, 1973. 2. Equivalent installations must be approved by the Chief, Engineering and Manufacturing Branch, Eastern Region, Jamaica, New York. 3. Upon submission of substantiating data by an owner or operator through an FAA Maintenance Inspector, the Chief, Engineering and Manufacturing Branch, FAA, Eastern Region, may adjust the compliance time specified in this A.D. This amendment is effective December 26, 1974.
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.
2001-01-13: This amendment adopts a new airworthiness directive (AD); applicable to all Boeing Model 737-300, -400, and -500 series airplanes. This AD requires, among other actions, a one-time detailed visual inspection of the fuel quantity indicating system (FQIS) wiring and fuel tubing on the inboard side of the right wing rib wing buttock line (WBL) 227 and on the aft side of stringer No. 13 to determine if clearance exists between the FQIS wire harness and the refuel tube and tube coupling, and to detect any loose or broken refuel tube clamp or bracket or chafing of the FQIS wire harness; and corrective actions, if necessary. This action is necessary to detect and correct chafing and to prevent electrical contact between the FQIS wiring and the surrounding structure, which, in conjunction with another wiring failure outside the fuel tank, could result in fire or explosion of the fuel tank. This action is intended to address the identified unsafe condition.
2018-03-19: We are adopting a new airworthiness directive (AD) for certain [[Page 6121]] Dassault Aviation Model FALCON 7X airplanes. This AD was prompted by a report indicating that fuselage panels were manufactured with defects that could reduce panel fatigue limits. This AD requires a one-time inspection of the affected panels and repair if necessary, and for certain airplanes, installation of a stiffener. We are issuing this AD to address the unsafe condition on these products.
2007-12-02: The FAA is adopting a new airworthiness directive (AD) for certain McDonnell Douglas airplanes described previously. This AD requires installing bonding jumpers to the airplane wing structure from the fuel system in-line electrical solenoid valves along the left and right wing front spar. This AD results from fuel system reviews conducted by the manufacturer. We are issuing this AD to prevent point- of-contact arcing or filament heating damage in the fuel lines that could create a potential ignition source, which, in combination with flammable fuel vapors, could cause a fuel tank explosion and consequent loss of the airplane.
2004-15-10: This amendment adopts a new airworthiness directive (AD), applicable to certain Saab Model SAAB SF340A series airplanes, that requires replacing certain power wires with a modification harness; and testing the new harness installation. These actions are necessary to prevent a momentary loss of data on the left-hand electronic flight instrumentation system (LH 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. This action is intended to address the identified unsafe condition.