Results
2018-24-05: We are adopting a new airworthiness directive (AD) for all Fokker Services B.V. Model F28 airplanes. This AD was prompted by reports that filters, which are integral to certain T-unions in the landing gear hydraulic control system, disconnected from their housing and, in some cases, migrated. This AD requires replacing certain T- unions with an integral filter with T-unions without an integral filter. We are issuing this AD to address the unsafe condition on these products.
98-18-20: This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 727 and Model 737 series airplanes, that requires replacement of the actuator of the engine fuel shutoff valve and the fuel system crossfeed valve with an improved actuator. This amendment is prompted by a report indicating that, during laboratory tests, the actuator clutch on the engine fuel shutoff and crossfeed valves failed to function properly. The actions specified by this AD are intended to prevent improper functioning of these actuators, which could result in a fuel imbalance due to the inability of the flightcrew to crossfeed fuel; improperly functioning actuators also could prevent the pilot from shutting off the fuel to the engine following an engine failure and/or fire.
48-29-01: 48-29-01 NAVION: Applies to All Airplanes Employing Carter Engine Driven Fuel Pumps Not Presently Equipped With Vent Drain Lines. To be accomplished as soon as possible but not later than October 15, 1948. Several instances of rupture of the main diaphragm of Carter fuel pumps have occurred. This is considered a fire hazard, since fuel can then squirt from the pump breather hole onto the engine. To correct this condition the pump breather should be provided with an overboard drain to carry fuel clear of the airplane if the diaphragm ruptures. Before installing the drain line, the fiber screen and snap ring must be removed from the pump breather opening. The drain line should vent into a low pressure area so that any fuel leaving this drain will not be in the proximity of any engine or cabin heater exhaust and will not contact the airplane or enter any air intake line, in ground or flight operation. (Ryan Navion Service Letter No. 47 covers this same subject.)
2002-16-09: This amendment adopts a new airworthiness directive (AD) that is applicable to all McDonnell Douglas Model 717-200 airplanes. This action requires repetitive tests to detect failure of the solenoid operated shut-off valve (SOV) of the inboard and outboard spoiler actuator assemblies, and corrective action if necessary. This action is necessary to detect and correct conditions associated with high electrical resistance in the solenoid, which, in combination with the failure of a spoiler actuator, could result in reduced controllability of the airplane. This action is intended to address the identified unsafe condition.
93-14-19R1: We are removing Airworthiness Directive (AD) 93-14-19, which applied to certain The Boeing Company Model 767-200 and -300 series airplanes. AD 93-14-19 required inspections for disbonding of the trailing edge wedge of the leading edge slat; and repair, if necessary. We issued AD 93-14-19 to prevent the loss of a trailing edge wedge, which could result in reduced maneuver margins, reduced speed margins to stall, and unexpected roll before stall warning, all of which would adversely affect the controllability of the airplane. Since we issued AD 93-14-19, an updated stability and control analysis showed that the worst-case scenario of a trailing edge wedge disbond in-flight would not adversely affect the controllability of the airplane. Accordingly, AD 93-14-19 is removed.
2018-22-13: We are adopting a new airworthiness directive (AD) for certain Airbus SAS Model A350-941 and -1041 airplanes. This AD was prompted by a technical issue detected on the inboard aileron electro-hydrostatic actuators that caused potential erroneous monitoring of those actuators. This AD requires revising the airplane flight manual to provide the flightcrew with updated procedures related to inboard aileron fault operations. We are issuing this AD to address the unsafe condition on these products.
94-04-08: This amendment adopts a new airworthiness directive (AD), applicable to certain McDonnell Douglas Model DC-10 series airplanes and Model KC-10A (military) airplanes, that requires inspections to detect cracking in the No. 2 engine pylon lower spar forward mount and thrust link fitting attach bolts, replacement of cracked bolts, and the eventual replacement of all bolts made of H-11 material with bolts made of Inconel. This amendment is prompted by reports of failures of these attach bolts due to stress corrosion. The actions specified by this AD are intended to prevent failure of the attach bolts, which could reduce the fail-safe capability of the attachment assembly.
2005-23-04: The FAA is adopting a new airworthiness directive (AD) for certain Saab Model SAAB 2000 airplanes. This AD requires modifying the manual feather-and-unfeather system for the propellers to make the design of the system more robust. This AD results from reports of in- flight engine shutdown caused by uncommanded operation of the feather pump of the propeller. We are issuing this AD to prevent uncommanded feathering of the propeller, which could result in the shutdown of an engine during flight and consequent reduced controllability of the airplane.
68-02-01: 68-02-01 BRISTOL SIDDELEY: Amendment 39-542. Applies to deHavilland Model Gipsy Queen Series 70 Engines with Crankshafts with Modifications 1399 (R.155), 1609 (R.259), 2289 (R.155 and R.259), 2931 (R.563 and R.564), or Repair Schemes R.155 and R.259 incorporated. Compliance required as indicated, unless already accomplished. To prevent failure of the crankshaft front end that could result in loss of the propeller, accomplish the following: (a) Within the next 400 hours' time in service after the effective date of this AD and thereafter at intervals not to exceed 400 hours' time in service from the last inspection, visually inspect the crankshaft for cracks, in accordance with Bristol Siddeley Technical News Sheet (TNS) G.Q. 70 No. 105, dated August 14, 1967, or later ARB-approved issue, or an FAA-approved equivalent. (b) If cracks are found during the inspections required by paragraph (a), replace cracked crankshaft before further flight with an uncracked crankshaft, or incorporate Gipsy Modification 2925 (R.550). If Gipsy Modification 2925 (R.550) is not incorporated, inspect the replacement crankshaft in accordance with paragraph (a). (c) If no cracks are found during the inspections required by paragraph (a), incorporate Modification 2925 (R.550), or an FAA-approved equivalent, at next overhaul. (d) The repetitive inspections required by paragraph (a) may be discontinued after the incorporation of Gipsy Modification 2925 (R.550). This amendment becomes effective February 16, 1968.
2002-19-52: This amendment supersedes an existing airworthiness directive (AD), applicable to all Boeing Model 737-600, -700, -700C, -800, and - 900 series airplanes; Model 747 series airplanes; and Model 757 series airplanes, that currently requires revision of the FAA-approved airplane flight manual (AFM) to advise the flight crew of certain operating restrictions for maintaining minimum fuel levels; prohibits use of the horizontal stabilizer tank on certain airplanes, and prohibits the installation of certain fuel pumps. This amendment requires concurrent removal of the currently required AFM revisions and insertion of new AFM revisions; requires installation of placards to alert the flightcrew to the operating restrictions; and prohibits installation of any uninspected pumps. This amendment permits the AFM revision and placard to be removed under certain conditions. The actions specified in this AD are intended to prevent fuel vapors from coming into contact with an ignition source inthe center wing fuel tank, horizontal stabilizer fuel tank, center auxiliary fuel tank (body tank), or auxiliary fuel tanks 1 and 4, which could result in fire/ explosion.
2018-20-11: We are adopting a new airworthiness directive (AD) for certain Bombardier, Inc., Model DHC-8-300 series airplanes. This AD was prompted by reports indicating that a certain emergency exit door could not be opened during maintenance. This AD requires a detailed inspection of the ball bearings of an emergency exit, replacement of bearings if necessary, application of corrosion inhibiting compound (CIC), and revision of the maintenance or inspection program, as applicable. We are issuing this AD to address the unsafe condition on these products.
2005-23-03: The FAA is adopting a new airworthiness directive (AD) for certain Learjet Model 23, 24, 24A, 24B, 24B-A, 24C, 24D, 24D-A, 24E, 24F, 24F-A, 25, 25A, 25B, 25C, 25D, and 25F airplanes. This AD requires replacement of the spherical accumulator for the main hydraulic system with a new cylindrical accumulator. For certain airplanes, this AD also requires modification of the accumulator pressure gauge. This AD results from reports of the failure of two thrust reverser accumulators (which are similar to the main hydraulic system's spherical accumulator) and fatigue cracks found on four thrust reverser accumulators. We are issuing this AD to prevent failure of the spherical accumulator for the main hydraulic system, due to fatigue cracking on the threads, which could result in the loss of hydraulic power, damage to the surrounding airplane structure, and loss of airplane control. The failure of the accumulator could also result in injury to any persons in the surrounding area. The loss of hydraulic fluid could also leak onto a potential source of ignition and result in a consequent fire.
81-13-51: 81-13-51 CANADAIR: Amendment 39-4268. Applies to all Canadair CL-600 series airplanes certified in all categories. To detect dragging wheel brakes, unless already accomplished, accomplish the following prior to further flight. A. Inspect and replace, if necessary, wheel brake assembly P/N 600-85083-55 with wheel brake assembly P/N 600-85083-57 in accordance with Canadair Alert Service Bulletin A600-0045, Revision 1, dated June 15, 1981. B. Airplanes may be flown to a maintenance base for repairs or replacement in accordance with FAR 21.197. C. Alternate means of compliance or other actions which provide an equivalent level of safety may be used when approved by the Chief, Seattle Area Aircraft Certification Office, FAA Northwest Mountain Region. The manufacturer's specifications and procedures identified and described in this directive are incorporated herein and made a part hereof pursuant to 5 U.S.C. 552(a)(1). All persons affected by this directive who have not already received these documents from the manufacturer may obtain copies upon request to the addresses listed above. These documents may also be examined at FAA Northwest Mountain Region, 9010 East Marginal Way South, Seattle, Washington 98108. This amendment becomes effective December 7, 1981 and was effective earlier to those recipients of Telegraphic AD T81-13-51 dated June 19, 1981.
2018-23-11: We are adopting a new airworthiness directive (AD) for certain Airbus SAS Model A319 series airplanes; Model A320-211, -212, -214, - 231, -232, and -233 airplanes; and Model A321-111, -112, -131, -211, - 212, -213, -231, and -232 airplanes. This AD was prompted by investigations that revealed that the cover seal of the brake dual distribution valve (BDDV) was damaged and did not ensure efficient sealing. This AD requires identifying the BDDV part number installed on the airplane, and modifying or replacing BDDVs having certain part numbers. We are issuing this AD to address the unsafe condition on these products.
98-18-22: This amendment adopts a new airworthiness directive (AD), applicable to certain McDonnell Douglas Model DC-9-10, -15, and -30 series airplanes, and C-9 (military) airplanes, that requires a one-time visual inspection to determine if all corners of the upper cargo doorjamb have been previously modified; various follow-on repetitive inspections; and modification, if necessary. This amendment is prompted by reports of fatigue cracks found in the fuselage skin and doubler at the corners of the upper cargo doorjamb. The actions specified by this AD are intended to detect and correct such fatigue cracking, which could result in rapid decompression of the fuselage and consequent reduced structural integrity of the airplane.
2018-22-05: We are adopting a new airworthiness directive (AD) for all Engine Alliance (EA) GP7270, GP7272, and GP7277 turbofan engines with a certain high-pressure turbine (HPT) case installed. This AD requires removal of affected HPT stator cases (HPT cases) from service and their replacement with a part eligible for installation. This AD was prompted by the discovery of a quality escape at a manufacturing facility involving unapproved welds on HPT cases. We are issuing this AD to address the unsafe condition on these products.
67-11-02: 67-11-02 FAIRCHILD-HILLER: Amdt. 39-385 Part 39 Federal Register April 5, 1967. Applies to Model F-27 Series Airplanes, Serial Numbers 1 through 19 Except Serial Numbers 7, 10, 13 and 17. Compliance required as indicated. To detect cracks in the lower fuselage exterior skins, accomplish the following: (a) Within the next 50 hours' time in service after the effective date of this AD, unless already accomplished within the last 350 hours' time in service, and thereafter at intervals not to exceed 400 hours' time in service from the last inspection, visually inspect the fuselage skins between stringers 7 and 8 left and stringers 44 and 45 right from Fuselage Station 198 to Station 510, or use an equivalent inspection approved by an FAA maintenance inspector. If cracks are found, comply with (b) before further flight, except that the airplane may be flown in accordance with FAR 21.197 to a base where the repair can be performed. (b) Repair cracked parts in accordance with Fairchild-Hiller Service Bulletin No. 53-48 dated February 7, 1967, or later revision approved by the Chief, Engineering and Manufacturing Branch, FAA Eastern Region, or equivalent approved by an FAA maintenance inspector, or replace them with an unused part of the same part number or an equivalent part approved by an FAA maintenance inspector. (c) The repetitive inspection required by (a) may be discontinued on those skin panels replaced in accordance with Fairchild-Hiller Service Bulletin No. 53-48, dated February 17, 1967, or later revision approved by the Chief, Engineering and Manufacturing Branch, FAA Eastern Region, or an equivalent modification approved by an FAA maintenance inspector. (d) Upon request of the operator, an FAA maintenance inspector, subject to prior approval of the Chief, Engineering and Manufacturing Branch, FAA Eastern Region, may adjust the initial compliance time and the repetitive inspection interval specified in this AD if the request contains substantiating data to justify the increase for that operator. This directive effective April 5, 1967.
2018-23-05: We are adopting a new airworthiness directive (AD) for certain Airbus SAS Model A350-941 and -1041 airplanes. This AD was prompted by a report of a close gap between the wing lower cover (WLC) and wing rib feet. This AD requires revising the operator's minimum equipment list (MEL) to change certain MEL items. This AD also requires an inspection for discrepancies and structural damage of certain wing rib foot locations, and related investigative and corrective actions if necessary. We are issuing this AD to address the unsafe condition on these products.
2011-15-10: We are adopting a new airworthiness directive (AD) for certain Superior Air Parts and Lycoming (formerly Textron Lycoming) fuel- injected engines. This AD requires removing from service, certain fuel servos. This AD was prompted by an accident involving a Piper PA32R- 301. We are issuing this AD to correct the unsafe condition on these products.
82-20-52: 82-20-52 BOEING VERTOL: Amendment 39-4480. Applies to Boeing Vertol Model 234 series helicopters, Manufacturer's Serial Numbers MJ001 through MJ006, equipped with forward transmission, P/N 234D1200-2, aft transmission, P/N 234D2200-2M, and combiner transmission, P/N 234D5200-5, certificated in all categories. Compliance is required prior to further flight, after the effective date of this AD, unless already accomplished. To prevent possible hazards in flight associated with transmission drive component failure, due to lubrication system contamination, accomplish the following: a. Remove the forward transmission, aft transmission and combiner transmission, disassemble, inspect and repair in accordance with the accomplishment instructions of Boeing Vertol Bulletin 234-65-1027, Revision 2 contained in Boeing Vertol TWX Nos. 8-1420-3-4264, - 4267, and 4273, respectively dated September 23, 24, and 25, 1982, or FAA approved equivalent. b. An equivalent method of compliance with this AD must be approved by the New York Aircraft Certification Office, FAA, New England Region, 181 South Franklin Avenue, Room 202, Valley Stream, New York 11581. This amendment becomes effective November 5, 1982.
84-24-04: 84-24-04 BF GOODRICH: Amendment 39-4960. Applies to BF Goodrich Emergency Evacuation Slide/Rafts P/N's 7A1340 series, 7A1342 series, 7A1371 series, and 7A1373 series installed on Boeing Model 747-100 and 747-200B airplanes in accordance with Supplemental Type Certificate (STC) SA574GL, and on Boeing Model 747-100B, 747SR, and 747-300 airplanes in accordance with STC SA575GL; and BF Goodrich Emergency Evacuation Slide/Rafts P/N's 7A1437 series, 7A1439 series, 7A1447 series, and 7A1448 series installed on Boeing Model 747-100 and 747-200B airplanes in accordance with STC SA744GL, and on Boeing Model 747-100B, 747SR, and 747-300 airplanes in accordance with STC SA745GL. \n\n\tCompliance is required as indicated, unless already accomplished. \n\n\tInspect and replace, as required, the girt bar attachment assemblies in accordance with the following: \n\n\tA.\tWithin the next 15 days after the effective date of this airworthiness directive (AD), inspect the applicable slide/rafts and replace the girt bar attachment assemblies in accordance with the procedures contained in BF Goodrich Alert Service Bulletin 25-093, Revision 1, dated November 21, 1984, or subsequent FAA approved revisions. \n\n\tB.\tDestroy the replaced girt bar attachment assemblies to preclude their installation at a later date. \n\n\tC.\tAlternate means of compliance with this AD which provide an equivalent level of safety may be used when approved by the Manager, Chicago Aircraft Certification Office, FAA, Central Region. \n\n\tD.\tSpecial flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate airplanes to a base for the accomplishment of inspections and/or modifications required by this AD. \n\n\tAll persons affected by this directive who have not already received these documents from the manufacturer may obtain copies upon request to BF Goodrich Company, Attn: Mr. David Smith, Dept. 1809, Bldg. 17F, 500 South Main Street, Akron, Ohio 44318; telephone (216) 374-2886. These documents also may be examined at the FAA, Northwest Mountain Region, 17900 Pacific Highway South, Seattle, Washington. \n\n\tThis amendment becomes effective December 17, 1984.
2005-23-06: The FAA is adopting a new airworthiness directive (AD) for certain Learjet Model 23, 24, 24A, 24B, 24B-A, 24D, 24D-A, 24E, 24F, 25, 25A, 25B, 25C, 25D, and 25F airplanes. This AD requires removing the thrust reverser accumulator, and making the thrust reverser hydraulic system and the thrust reversers inoperable. This AD results from reports of the failure of two thrust reverser accumulators. We are issuing this AD to prevent failure of the thrust reverser accumulators, due to fatigue cracking on the female threads, which could result in the loss of hydraulic power and damage to the surrounding airplane structure.
98-19-16: This amendment adopts a new airworthiness directive (AD), applicable to certain Aerospatiale Model ATR72-212A series airplanes, that requires installation of bushings on the lower attachment fittings of the flap support beam. 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 prevent rupture of the lower attachment fittings of the flap support beam due to fatigue, and consequent damage to the flaps; these conditions could result in reduced controllability of the airplane.
2017-23-10: We are superseding Airworthiness Directive (AD) 2017-19-17, which applied to certain Dassault Aviation Model FALCON 900EX and FALCON 2000EX airplanes. AD 2017-19-17 required revising the airplane flight manual (AFM) to include procedures to follow when an airplane is operating in icing conditions. AD 2017-19-17 also required a detailed inspection of the wing anti-ice system ducting for the presence of a diaphragm, and follow-on actions (replacement of ducting or re- identification of the ducting part marking). This new AD retains the actions required by AD 2017-19-17, and corrects the follow-on actions for certain airplanes. This AD was prompted by a determination that the follow-on actions specified in AD 2017-19-17 were incorrect for certain airplanes. We are issuing this AD to address the unsafe condition on these products.
2005-23-09: The FAA is adopting a new airworthiness directive (AD) for General Electric Company (GE) CF6-80E1A1, -80E1A2, -80E1A3, -80E1A4, and -80E1A4/B turbofan engines. This AD requires initial and repetitive fluorescent-penetrant inspections (FPI) of certain areas of high pressure compressor (HPC) cases, part number (P/N) 1509M97G07 and P/N 2083M69G03. This AD results from the discovery that HPC cases, P/N 1509M97G07 and P/N 2083M69G03, were inadvertently left out of the Airworthiness Limitations Section (ALS), Chapter 05-21-02, of GE Engine Manual, GEK 99376, Revision 17. We are issuing this AD to prevent failure of the HPC case aft mount flange, due to cracking.