Results
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.
2001-02-01: This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 737-300, -400, and -500 series airplanes, that requires repetitive inspections to detect cracking of certain areas of the forward pressure bulkhead, and repair, if necessary. This amendment also requires certain preventive modifications, which, when accomplished, terminate the repetitive inspections for the affected areas. This action is necessary to prevent fatigue cracking on critical areas of the forward pressure bulkhead, which could result in rapid decompression of the airplane fuselage. This action is intended to address the identified unsafe condition.
2001-01-12: This amendment adopts a new airworthiness directive (AD), applicable to all CASA Model CN-235, CN-235-100, and CN-235-200 series airplanes, that requires replacing the upper brackets in frames 33, 34, and 35, with improved brackets that are more fatigue resistant, and reinforcing frame 35. The actions specified by this AD are intended to prevent fatigue cracking in the zone of the fittings connecting the fuselage to stiffener rods located in frames 33, 34, and 35, which could result in reduced structural integrity of the airplane. This action is intended to address the identified unsafe condition.
73-09-06: 73-09-06 PIPER: Amendment 39-1631. Applies to Model PA-22-150, PA-22S-150, PA-22-160 and PA-22S-160 aircraft equipped with Lycoming O-320 series engines and Marvel Schebler Carburetors Model MA-4-SPA, Part Numbers 10-3678-11, 10-3678-12, 10-3678-32, and to other PA-22 type aircraft which have been modified to these engine/carburetor configurations. Compliance required within the next 10 hours in service after the effective date of this AD, unless already accomplished. To prevent power interruption and acceleration hangup resulting from abrupt throttle movement, accomplish the following: Attach the following operating limitation placard to the instrument panel near the throttle in full view of the pilot. Use 1/8 inch min. size lettering. "DO NOT OPEN THROTTLE RAPIDLY - (IDLE TO FULL THROTTLE, 2 SECONDS MINIMUM)" The placard may be fabricated by the owner or operator. This amendment is effective May 7, 1973.
2007-12-09: The FAA is adopting a new airworthiness directive (AD) for General Electric Company (GE) CF34-10E series turbofan engines. This AD requires revising the combustor case published life limit and removing combustor cases from service before reaching a reduced life limit. This AD results from GE's evaluation of the effects to the combustor case due to installing version 5.10 software in the full-authority digital electronic control (FADEC), and revising the combustor case published life limit. We are issuing this AD to prevent uncontained combustor case failure resulting in an in-flight engine shutdown and possible damage to the airplane.
72-11-01: 72-11-01 PIPER AIRCRAFT: Amdt. 39-1448. Applies to PA-23-235, PA-23-250, and PA-E23-250 series airplanes Serial Numbers 27-1 through 27-4765 inclusive, equipped with non-supercharged engines, including airplanes modified in accordance with STC SA179CE and STC SA867SW and certificated in all categories. Compliance required as indicated. In order to prevent possible explosion and fire resulting from fuel vapor ignition during engine starting, accomplish the following: a. Serial Numbers 27-1 through 27-2504 inclusive: Prior to first flight of each day, visually check the lower surface of the wings in the areas of the fuel cells and aft nacelle for fuel stains and any odor of fuel vapor. If fuel stains or any other sign of fuel leakage are observed, the source of leakage must be determined and repairs or replacements accomplished prior to further flight, in accordance with Section IX of Piper Service Manual No. 753464 or an equivalent repair approved by the Chief, Engineering and Manufacturing Branch, FAA Eastern Region. b. Serial Numbers 27-2505 through 27-4765 inclusive: Inspect in accordance with paragraph (a) above within 50 hours' time in service after the effective date of this AD or since the last inspection and every 50 hours thereafter. c. The checks required by paragraphs (a) and (b) above may be performed by the pilot, including pilots of aircraft engaged in Air Carrier operations. A chronological listing of compliance with this AD must be made in the airplane's permanent maintenance log in accordance with FAR 91.173. d. When the instruction paragraph contained in Piper Service Letter No. 606 is complied with or equivalent inspections and alterations approved by the Chief, Engineering and Manufacturing Branch, FAA Eastern Region, further compliance with this AD is not required. (Piper Service Letters Nos. 449 and 449A refer to this subject.) This AD supersedes AD 70-03-08. This amendment is effective May19, 1972.
2000-26-06: This amendment supersedes an existing airworthiness directive (AD) that applies to Eurocopter Deutschland GMBH (ECD) Model MBB-BK 117 helicopters. That AD currently requires, before further flight, creating a component log card or equivalent record and determining the calendar age and number of flights on each tension-torsion (TT) strap. This amendment establishes a life limit for certain main rotor TT straps. This amendment is prompted by an accident in which a main rotor blade (blade) separated from an ECD Model MBB-BK 117 helicopter due to fatigue failure of a TT strap. The actions specified by this AD are intended to prevent fatigue failure of a TT strap, loss of a blade, and subsequent loss of control of the helicopter.
2019-12-10: The FAA is adopting a new airworthiness directive (AD) for all Fokker Services B.V. Model F28 Mark 0070 and 0100 airplanes. This AD was prompted by a determination that new or more restrictive airworthiness limitations are necessary. This AD requires revising the existing maintenance or inspection program, as applicable, to incorporate new or more restrictive airworthiness limitations. The FAA is issuing this AD to address the unsafe condition on these products.
2007-11-20: The FAA is adopting a new airworthiness directive (AD) for GE CF6-80 series turbofan engines with fuel shroud retaining rings, part number (P/N) J204P0084, installed. This AD requires replacing those retaining rings with a more robust design fuel shroud retaining snap ring. This AD results from two events of external engine fuel leakage and a subsequent under-cowl engine fire. We are issuing this AD to prevent an under-cowl engine fire and damage to the airplane during an engine high vibration event.
2017-14-09: We are adopting a new airworthiness directive (AD) for all Fokker Services B.V. Model F28 Mark 0100 airplanes. This AD was prompted by an evaluation by the design approval holder (DAH) indicating that certain wing fuel tank access panels are subject to widespread fatigue damage (WFD). This AD requires replacement of affected access panels and modification of the coamings of the associated access holes. We are issuing this AD to address the unsafe condition on these products.
2004-11-06: This amendment adopts a new airworthiness directive (AD) for the specified Agusta S.p.A. (Agusta) model helicopters that requires disabling certain windshield wipers and thereafter modifying the electrical system of the windshield wipers by installing a new resistor and condenser, eliminating incompatibility problems with the relays, and replacing the timed relay for certain windshield wiper kits. This amendment is prompted by testing that revealed overheating of the electrical resistor on the electrical system of the windshield wipers due to a system overload because of a partial incompatibility of new timed relays with the configuration of the windshield wiper electrical system. The actions specified by this AD are intended to prevent the incompatibility of certain relays with the windshield wiper electrical system, overheating of the resistor due to system overload, and an electrical fire.
2001-01-10: This amendment adopts a new airworthiness directive (AD) that is applicable to all Boeing Model 747-400, 747-400F, 767-200, and 767-300 series airplanes equipped with Pratt & Whitney Model PW4000 series engines. This action requires revising the Airplane Flight Manual (AFM). This action is necessary to prevent reduced acceleration and climb performance relative to performance data in the AFM, which could result in runway overruns or impact with obstacles or terrain. This action is intended to address the identified unsafe condition.
2007-11-17: The FAA is superseding an existing airworthiness directive (AD), which applies to certain Cessna Model 500, 550, S550, 560, 560XL, and 750 airplanes. That AD currently requires installing identification sleeves on the wires for the positive and negative terminal studs of the engine and/or auxiliary power unit (APU) fire extinguishing bottles, as applicable, and re-connecting the wires to the correct terminal studs. This new AD retains the requirements of the existing AD; adds airplanes to the applicability; and, for certain airplanes only, requires a review of wiring changes made using the original issue of one service bulletin and corrective actions if necessary. This AD results from a determination that additional airplanes are subject to the unsafe condition described in the existing AD. We are issuing this AD to ensure that the fire extinguishing bottles are activated in the event of an engine or APU fire, and that flammable fluids are not supplied during a fire, which could result in an unextinguished fire in the nacelle or APU. DATES: This AD becomes effective July 6, 2007. The Director of the Federal Register approved the incorporation by reference of a certain publication listed in the AD as of July 6, 2007. On March 24, 2006 (71 FR 8443, February 17, 2006), the Director of the Federal Register approved the incorporation by reference of certain other publications listed in the AD.
2001-01-04: This amendment adopts a new airworthiness directive (AD) for Sikorsky Aircraft Corporation (Sikorsky) Model S-76A, S-76B, and S-76C helicopters. This AD requires initial and repetitive inspections of the main landing gear positioning rod assembly (rod assembly) and the side brace rod end (rod end) for corrosion. If any corrosion is found, this AD requires replacing any part that is corroded with an airworthy part before further flight. This amendment is prompted by a landing gear collapse caused by corrosion due to dissimilar metals in the landing gear rod end. The actions specified in this AD are intended to detect corrosion of the threaded joint in the rod assembly to prevent a collapse of the landing gear, and subsequent loss of control of the helicopter during landing.
2018-02-20: We are adopting a new airworthiness directive (AD) for certain The Boeing Company Model 777-200, -200LR, -300, and -300ER series airplanes. This AD was prompted by reports of corrosion in the aft fuselage. This AD requires a one-time review of the operator's maintenance procedures, repetitive detailed internal and external inspections for corrosion or cracking, and applicable on-condition actions. This AD also includes an optional terminating action for the inspections. We are issuing this AD to address the unsafe condition on these products.
2001-01-06: This amendment supersedes an existing airworthiness directive (AD), applicable to certain Airbus Industrie Model A300, A300-600, and A310 series airplanes; equipped with Dowty ram air turbines (RAT). That AD currently requires repetitive deployment tests of the RAT and checks of the adjustment of the locking rod. This amendment also requires modification of the RAT, which terminates the repetitive tests and checks. This amendment is prompted by issuance of mandatory continuing airworthiness information by a foreign civil airworthiness authority. The actions specified by this AD are intended to ensure the availability of the RAT in case of need.
2019-12-07: The FAA is superseding Airworthiness Directive (AD) 2007-11-11 and AD 2017-01-11, which applied to all Airbus SAS Model A318 and Model A319 series airplanes; Model A320-211, -212, -214, -231, -232, and -233 airplanes; and Model A321 series airplanes. AD 2007-11-11 required an inspection to determine the serial number of both main landing gear (MLG) sliding tubes, repetitive inspections for cracking of the affected MLG sliding tubes and corrective actions if necessary, and eventual replacement of both MLG shock absorbers. AD 2017-01-11 required identification of the part number and serial number of the MLG sliding tubes; inspection of affected chromium plates and sliding tube axles for damage; and replacement of the sliding tube if [[Page 30580]] necessary. This AD retains certain requirements of AD 2007-11-11 and AD 2017-01-11. This AD also requires repetitive inspections of affected MLG sliding tubes for cracking, replacement of cracked MLG sliding tubes, and eventualreplacement of each affected MLG sliding tube. This AD was prompted by cracks found in the MLG sliding tubes due to certain manufacturing defects that might not be identified using the current on-wing scheduled inspections. The FAA is issuing this AD to address the unsafe condition on these products.
72-01-07: 72-01-07 PIPER: Amdt. 39-1369 as amended by Amendment 39-1434. Applies to Piper Model PA-18, PA-18-105, -125, -135, PA-18A, PA-18A-125, -135, and seaplane versions of those models which have been modified after May 14, 1968 in accordance with Supplemental Type Certificate SA 136 AL to incorporate the installation of the Lycoming O-320 engine (150 HP). Factory delivered models having serial numbers 18-3771 and 18-3781 and above, incorporating the O-320 engine, are not affected by this AD. Compliance is required as indicated. To prevent possible failure of the engine mount, within the next 25 hours' time in service after the effective date of this AD, unless already accomplished, install engine mount, P/N 12351- 12, in accordance with Piper Drawing Number 12351, Mount Assembly-engine, including Revision J dated January 16, 1968, or an equivalent approved by the Chief, Engineering and Manufacturing Branch of an FAA region (or in the case of the Western Region, the Chief,Aircraft Engineering Division). NOTE: Engine mount assembly P/N 12351-12 may be identified by the gage of Tube "A" and Tube "B" which measure .049 inches, and by the incorporation of two reinforcing plates, number 14438, mounted at the lower right engine attachment points as shown on Piper Drawing Number 12351, Mount Assembly-Engine, including Revision J dated January 16, 1968. Amendment 39-1369 became effective January 27, 1972. This Amendment 39-1434 becomes effective April 17, 1972.