Results
88-13-07: 88-13-07 SHORT BROTHERS, PLC: Amendment 39-5950. Applies to Model SD3-30 series airplanes; serial numbers SH3002 through SH3096, inclusive; certificated in any category. Compliance required as indicated, unless previously accomplished. To prevent pitot tubes from becoming inoperative due to icing, which could result in erroneous airspeed and altitude indication, accomplish the following: A. Within the next 180 days after the effective date of this AD, replace pitot tubes having the code letter "Z" adjacent to the serial number with one containing a code letter other than "Z", in accordance with accomplishment instructions in Service Bulletin SD3-34-26, Revision 1, dated September 1, 1985. B. An alternate means of compliance or adjustment of the compliance time, which provides an acceptable level of safety and which has the concurrence of an FAA Principal Maintenance Inspector, may be used when approved by the Manager, Standardization Branch, ANM-113, FAA, Northwest Mountain Region. NOTE: The request should be forwarded through an FAA Principal Maintenance Inspector (PMI), who may add any comments and then send it to the Manager, Seattle Aircraft Certification Office. C. Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate airplanes to a base for the accomplishment of the requirements required by this AD. All persons affected by this directive who have not already received the appropriate service information from the manufacturer may obtain copies upon request to Short Brothers, PLC, Service Representative, 2011 Crystal Drive, Suite 713, Arlington, Virginia 22202-3702. This information may be examined at the FAA, Northwest Mountain Region, 17900 Pacific Highway South, Seattle, Washington, or the Seattle Aircraft Certification Office, 9010 East Marginal Way South, Seattle, Washington. This amendment, 39-5950, becomes effective July 11, 1988.
2004-26-08: The FAA is adopting a new airworthiness directive (AD) for certain Bombardier Model CL-215-6B11 (CL215T variant) and CL-215-6B11 (CL415 variant) series airplanes. This AD requires replacing the mounting pad studs of the auxiliary feather pump with new, longer studs, and installing a pressure relief valve. This AD is prompted by a few incidents of external oil leaks from the oil pump of the power control unit due to a malfunction of the pressure regulating valve. We are issuing this AD to prevent fracturing of the pump body, which could result in loss of engine oil, and consequent inability to maintain engine oil pressure and to feather the propeller.
2014-15-14: We are superseding Airworthiness Directive (AD) 89-12-10, for certain The Boeing Company Model 747 airplanes. AD 89-12-10 required replacement of certain underwing fuel tank access doors with stronger, fire-resistant doors. This new AD requires inspecting certain fuel tank access doors for installation of impact-resistant doors, and stencils and index markers; corrective actions if necessary; revising the maintenance program to incorporate certain new airworthiness limitations; and adding airplanes to the applicability. This AD was prompted by a report of a standard access door installed instead of an impact-resistant access door and stencils missing from some impact- resistant access doors and adjacent wing skin. We are issuing this AD to prevent foreign object penetration of the fuel tank, which could cause a fuel leak near an ignition source (e.g., hot brakes or engine exhaust nozzle), consequently leading to a fuel-fed fire.
2005-01-02: The FAA is adopting a new airworthiness directive (AD) for certain Lockheed Model 1329 series airplanes. This AD requires repetitive inspections to detect crack damage in the front spar cap assembly of the lower vertical stabilizer; reworking the spar cap doublers if no crack damage is found during any inspection; and repairing if any crack damage is found during any inspection. This AD is prompted by reports of cracks in the front spar cap assembly of the lower vertical stabilizer at box beam station 24 on the aft side of the 25% chord line. We are issuing this AD to find and fix cracks in the front spar cap assembly of the lower vertical stabilizer, which could result in rapid crack propagation and failure of the front spar cap. Failure of the front spar cap could lead to loss of rudder control and consequent reduced controllability of the airplane.
88-04-09: 88-04-09 BOEING: Amendment 39-5854. Applies to Model 767 series airplanes, as listed in Boeing Service Bulletin 767-36-0021, dated September 17, 1987, certificated in any category. Compliance required within the next six months after the effective date of this AD, unless already accomplished. \n\n\tTo preclude engine or pneumatic system damage caused by failure of the pneumatic system 8th stage check valve, accomplish the following: \n\n\tA.\tWithin the next 6 months after the effective date of this AD, inspect the pneumatic system 8th stage check valves on both engines, in accordance with Boeing Service Bulletin 767-36-0021, dated September 17, 1987, or later FAA-approved revision, to determine if the serial numbers are among those listed in Hamilton Standard Service Bulletin 36-2056, dated June 29, 1987, or later FAA-approved revision, as requiring further inspection. \n\n\tB.\tIf any valve is identified by serial number as requiring further inspection, prior to further flight, remove the valve from the airplane, inspect the valve retention collar and, if necessary, modify the valve in accordance with the above mentioned service bulletins. \n\n\tC.\tValves not installed on an airplane must be inspected, and modified if necessary, in accordance with the above-mentioned service bulletins, prior to their installation on airplanes. \n\n\tD.\tAn alternate means of compliance or adjustment of the compliance time, which provide an acceptable level of safety, and which has the concurrence of an FAA Principal Maintenance Inspector, may be used when approved by the Manager, Seattle Aircraft Certification Office, FAA, Northwest Mountain Region. \n\n\tE.\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 the rework required by this AD. \n\n\tAll persons affected by this directive who have not already received the appropriate service documents from the manufacturer may obtain copies upon request to the Boeing Commercial Airplane Company, P.O. Box 3707, Seattle, Washington 98124-2207. These documents may be examined at the FAA, Northwest Mountain Region, 17900 Pacific Highway South, Seattle, Washington, or the Seattle Aircraft Certification Office, 9010 East Marginal Way South, Seattle, Washington. \n\n\tThis amendment becomes effective April 5, 1988.
86-14-01: 86-14-01 SPERRY CORPORATION, AEROSPACE AND MARINE GROUP: Amendment 39-5340. Applies to Sperry Corporation AHZ-600 Attitude Heading Reference System (AHRS), known to be installed in, but not limited to, DeHavilland Model DHC-8, British Aerospace Model BAe 125-800, Cessna Model 650, and Aerospatiale Model ATR-42 series airplanes, certificated in any category. Compliance is required within 30 days after the effective date of this AD, unless previously accomplished. To prevent loss of attitude/heading reference information, accomplish the following: A. Modify the Sperry Corporation AH-600 Strapdown Attitude and Heading Reference Unit (AHRU) by incorporating modifications in accordance with the following Sperry Service Bulletins or later revisions approved by the Manager, Western Aircraft Certification Office, FAA, Northwest Mountain Region: 21-1985-175, dated April 7, 1986 (Modification T); 21-1985-186, dated April 7, 1986 (Modifications S & V); 21-1985-187,dated April 7, 1986 (Modification U); 21-1986-19, dated April 22, 1986 (Modification Z); 21-1986-20, dated April 22, 1986 (Modification AA); and 21-1986-29, dated April 22, 1986 (Modification AB). B. Alternate means of compliance which provide an acceptable level of safety may be used when approved by the Manager, Western Aircraft Certification Office, FAA, Northwest Mountain Region. C. Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate airplanes to a base in order to comply with the requirements of this AD. All persons affected by this directive who have not already received the appropriate service documents from the manufacturer may obtain copies upon request to Sperry Corporation, Aerospace & Marine Group, P.O. Box 29000, Phoenix, Arizona 85038-9000. These documents may be examined at the FAA, Northwest Mountain Region, 17900 Pacific Highway South, Seattle, Washington, or the Western Aircraft Certification Office,15000 Aviation Boulevard, Hawthorne, California. This amendment becomes effective July 14, 1986.
2005-01-01: This amendment supersedes an existing airworthiness directive (AD), applicable to certain Airbus Model A319 and A320-200 series airplanes, that currently requires repetitive inspections to detect loose, missing, or discrepant rivets in specified areas of the door frames of the overwing emergency exits; measurement of the grip length of all rivets in the specified areas; and corrective action if necessary, which terminates the repetitive inspections. This new amendment also requires an inspection for correct dimensions of the interior countersinks of the rivet holes, and related corrective action. The actions specified by this AD are intended to prevent loose, missing, or discrepant rivets, which could lead to reduced structural integrity of the door frames of the overwing emergency exits. This action is intended to address the identified unsafe condition.
2023-10-09: The FAA is adopting a new airworthiness directive (AD) for all The Boeing Company Model 787-8, 787-9, and 787-10 airplanes. This AD was prompted by reports of damaged decompression panels from operators. This AD requires repetitive inspections for damaged fastener holes on the vertical and bottom edges of the inward and outward blowing decompression panels installed on the forward and aft cargo compartment vertical sidewall linings and applicable on-condition actions. The FAA is issuing this AD to address the unsafe condition on these products.
2023-11-06: The FAA is adopting a new airworthiness directive (AD) for certain Engine Alliance (EA) Model GP7270, GP7272, and GP7277 engines. This AD was prompted by a manufacturer investigation that revealed that certain high-pressure turbine (HPT) interstage seals were manufactured from material suspected to contain iron inclusion. This AD requires replacement of the affected HPT interstage seals. The FAA is issuing this AD to address the unsafe condition on these products.
82-06-04: 82-06-04 CANADAIR: Amendment 39-4344. Applies to Model CL-600 airplanes serial numbers 1005, 1007, 1011 thru 1013, and 1016 thru 1019, certificated in all categories. To prevent jamming of the main entry door unlatching system, accomplish the following, unless already accomplished. 1. Within the next 25 hours time in service after the effective date of this AD, perform the door handle operation check and handle adjustments described in paragraph 2 of Canadair Alert Service Bulletin A600-0077 dated July 27, 1981. 2. Replace the existing clear plastic handle guard, Part Number 600-31710-1, with guard assembly, Part Number 600-31772-1, in accordance with paragraph 2 of Canadair Alert Service Bulletin A600-0074 dated July 20, 1981. 3. Ensure that the internal door "EMERGENCY EXIT" placard located to the left hand side of the inner door handle is an approved placard reading as follows: EMERGENCY EXIT PULL AND TURN HANDLE TO "OPEN" PUSH DOOR 4.Airplanes may be flown in accordance with FAR 21.197 to a maintenance base for accomplishment of the inspection required by this AD. 5. Alternate methods of compliance with this AD may be used when they provide an equivalent level of safety and are 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). This amendment becomes effective March 22, 1982.
2000-09-11: This amendment adopts a new airworthiness directive (AD), applicable to certain Fokker Model F.28 Mark 0070 series airplanes. This action requires a one-time inspection to detect loose bolts attaching the gustlock counter-bracket to the pulley on the elevator tension regulator assembly, and corrective action, if necessary. This amendment is prompted by issuance of mandatory continuing airworthiness information by a foreign civil airworthiness authority. The actions specified in this AD are intended to prevent restricted elevator movement and consequent reduced controllability of the airplane.
2005-01-05: The FAA is superseding an existing airworthiness directive (AD), which applies to certain EMBRAER Model EMB-135 and EMB-145 series airplanes. That AD currently requires replacing the nose landing gear wheel nuts and associated inner and outer seals, and reidentifying the landing gear strut. This new AD adds an airplane to the applicability and revises a part number for a replacement part. This AD is prompted by a report of an invalid part number for the new nose landing gear wheel nut. We are issuing this AD to prevent separation of the wheels from the nose landing gear due to the failure of the outer wheel bearings, and consequent loss of control of the airplane during takeoff and landing.
86-19-08: 86-19-08 MCDONNELL DOUGLAS: Amendment 39-5405. Applies to McDonnell Douglas Model DC-10-10, -15, -30, -40, and KC-10A (Military) series airplanes, certificated in any category. \n\n\tCompliance required as indicated unless previously accomplished. \n\n\tTo assure proper operation of the right-hand forward passenger emergency exit operating handle, accomplish the following: \n\n\tA.\tWithin the next 12 months after the effective date of this AD, modify, reidentify, and reinstall the right-hand forward door assembly and escutcheon assembly in accordance with the Accomplishment Instructions of McDonnell Douglas DC-10 Service Bulletin 25-339, dated December 4, 1985, or later revisions approved by the Manager, Los Angeles Aircraft Certification Office, FAA, Northwest Mountain Region. \n\n\tB.\tAlternate means of compliance which provide an acceptable level of safety may be used when approved by the Manager, Los Angeles Aircraft Certification Office, FAA, Northwest Mountain Region. \n\n\tC.\tSpecial flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate airplanes to a base in order to comply with the requirements of this AD. \n\n\tAll persons affected by this directive who have not already received the appropriate service documents from the manufacturer may obtain copies upon request to McDonnell Douglas Corporation, 3855 Lakewood Boulevard, Long Beach, California 90846, Attention: Director, Publications and Training, C1-L65 (54-60). These documents may be examined at the FAA, Northwest Mountain Region, 17900 Pacific Highway South, Seattle, Washington, or the Los Angeles Aircraft Certification Office, 4344 Donald Douglas Drive, Long Beach, California. \n\n\tThis Amendment becomes effective October 2, 1986.
2023-11-02: The FAA is adopting a new airworthiness directive (AD) for all Airbus SAS Model A300 B4-600, B4-600R, and F4-600R series airplanes, and Model A300 C4-605R Variant F airplanes (collectively called Model A300-600 series 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, as specified in a European Union Aviation Safety Agency (EASA) AD, which is incorporated by reference. The FAA is issuing this AD to address the unsafe condition on these products.
2014-13-14: We are adopting a new airworthiness directive (AD) for certain Airbus Model A310 series airplanes. This AD was prompted by a report of an electrical arc and a hydraulic haze in the wheel bay of the left- hand main landing gear (MLG), possibly resulting from chafing between a hydraulic high pressure hose and electrical wiring of the green electrical motor pump (EMP). This AD requires modification of the electrical routing and replacement of the union elbows. We are issuing this AD to prevent chafing of hydraulic pressure hoses and electrical wiring of the green EMPs, which, in combination with a system failure, could cause an uncontrolled and undetected fire in the MLG bay.
2009-06-11: 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 aircraft structure fatigue tests, cracks were found in the wing lower skin stringers between ribs 7 and 10 on both wings. In order to prevent fatigue cracks in the wing lower skin stringers, which could result in fuel leakage and reduced structural integrity of the wing, the referred stringers must be reworked. We are issuing this AD to require actions to correct the unsafe condition on these products.
2004-26-09: The FAA is adopting a new airworthiness directive (AD) for Rolls-Royce Corporation (RRC) 250-B and 250-C series turboprop and turboshaft engines with certain part numbers (P/Ns) of compressor adaptor couplings manufactured by Alcor Engine Company (Alcor), EXTEX Ltd. (EXTEX), RRC, and Superior Air Parts (SAP) installed. This AD requires operators to remove from service affected compressor adaptor couplings. This AD results from nine reports of engine shutdown caused by coupling failure. We are issuing this AD to reduce the risk of failure of the compressor adaptor coupling and subsequent loss of all engine power.
2014-15-10: We are adopting a new airworthiness directive (AD) for certain Dassault Aviation Model FALCON 7X airplanes. This AD was prompted by a report of a crew alerting system message caused by an inversion of the wiring in the slats control manifold (SCM). This AD requires an operational test of the SCM, and replacing the affected SCM with a serviceable SCM if necessary. We are issuing this AD to detect and correct inversion of the wiring in the SCM, which could lead to a commanded retraction of the median and outboard slats in flight, and result in reduced controllability of the airplane.
88-24-12: 88-24-12 BOEING: Amendment 39-6068. Applies to all Model 727 series airplanes, prior to line number 1620, not equipped with the safety bar modification described in Boeing Service Bulletin 727-32-275, Revision 2, dated March 30, 1984, certificated in any category. Compliance required within the next 3,500 flight cycles after the effective date of this AD, unless previously accomplished. \n\n\tTo prevent failure of the main landing gear (MLG) to extend as a result of loosening of the self-locking nut at the attachment of the downlock forward pushrod assembly to the downlock torque shaft, accomplish the following: \n\n\tA.\tModify airplanes listed in Boeing Service Bulletin 727-32-0237, Revision 5, dated July 7, 1988, by installing the bolt, washer, nut, and cotter pin called out in item 5 of Figure 5 of that service bulletin. \n\n\tB.\tModify airplanes listed in Boeing Service Bulletin 727-32-0353, Revision 1, dated July 7, 1988, by installing the bolt, washer, nut, and cotter pin in accordance with that service bulletin. \n\n\tC.\tAn alternate means of compliance or adjustment of the compliance time, which provides an acceptable level of safety, may be used when approved by the Manager, Seattle Aircraft Certification Office, FAA, Northwest Mountain Region. \n\n\tNOTE: The request should be forwarded through an FAA Principal Maintenance Inspector (PMI), who may add any comments and then send it to the Manager, Seattle Aircraft Certification Office. \n\n\tD.\tSpecial flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate airplanes to a base in order to comply with the requirements of this AD. \n\n\tAll persons affected by this directive who have not already received the appropriate service documents from the manufacturer may obtain copies upon request to Boeing Commercial Airplanes, P.O. Box 3707, Seattle, Washington 98124. These documents may be examined at the FAA, Northwest Mountain Region, 17900 Pacific Highway South, Seattle Washington, or Seattle Aircraft Certification Office, FAA, Northwest Mountain Region, 9010 East Marginal Way South, Seattle, Washington. \n\n\tThis amendment, 39-6068, becomes effective December 23, 1988.
97-02-16: This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 737-300, -400, and -500 series airplanes, that requires modification of the system that detects a loss of tension in the cable controlling the flaps by removing the shim from behind the proximity switch and by trimming the switch bracket. This amendment is prompted by reports that the switch bracket can impair the movement of a pulley arm mechanism, ultimately preventing the detection system from operating. The actions specified by this AD are intended to prevent such impairment, which could result in movement of the flaps without action by the pilot, and ultimately cause reduced controllability of the airplane.
2004-26-03: The FAA is superseding an existing airworthiness directive (AD) for Rolls-Royce plc (RR) models RB211-535E4-37, RB211-535E4-B-37, RB211-535C-37, RB211-535E4-B-75, and RB211-22B-02 turbofan engines. That AD currently requires inspecting certain high pressure (HP) turbine discs, manufactured between 1989 and 1999, for cracks in the rim cooling air holes, and, if necessary, replacing the disc's serviceable parts. This AD requires the same actions but at reduced compliance schedules and adds the RR model RB211-535E4-C turbofan engine to the applicability. This AD results from a report of cracks in a model RB211-524 HP turbine disc that had propagated further than expected. We are issuing this AD to prevent possible disc failure, which could result in an uncontained engine failure and damage to the airplane.
2023-10-01: The FAA is adopting a new airworthiness directive (AD) for certain Embraer S.A. Model ERJ 190-300 and ERJ 190-400 airplanes. This AD was prompted by the excessive operation of certain elevator and rudder surfaces during manufacturing, causing damage and accelerating wear of internal parts of the power control units (PCUs). This AD requires replacement of the left-hand (LH) and right-hand (RH) elevator PCUs and lower and upper rudder PCUs, as specified in an Ag[ecirc]ncia Nacional de Avia[ccedil][atilde]o Civil (ANAC) AD, which is incorporated by reference. The FAA is issuing this AD to address the unsafe condition on these products.
92-02-14 R1: The FAA is removing Airworthiness Directive (AD) 92-02-14, which applied to certain Airbus SAS Model A320 series airplanes. AD 92- 02-14 required inspection for correct installation of the flexible control cables on the overwing emergency escape slides. The FAA issued AD 92-02-14 to prevent failure of the overwing emergency escape slides to deploy, which would compromise use of the exit during an emergency. Since the FAA issued AD 92-02-14, no new occurrences of incorrect cable installations have been reported, and existing maintenance activities are adequate to prevent new occurrences. Therefore, the FAA has determined that AD 92-02-14 is no longer necessary. Accordingly, AD 92- 02-14 is removed.
2004-25-23: This amendment adopts a new airworthiness directive (AD), applicable to all Boeing Model 747 series airplanes, that requires repetitive inspections for cracking of the top and side panel webs and panel stiffeners of the nose wheel well (NWW), and corrective actions if necessary. This action is necessary to detect and correct fatigue cracks in the top and side panel webs and stiffeners of the NWW, which could compromise the structural integrity of the NWW and could lead to the rapid depressurization of the airplane. This action is intended to address the identified unsafe condition.
2000-23-21: This amendment supersedes emergency airworthiness directive (AD) 2000-08-51. Emergency AD 2000-08-51 was sent to all known U.S. owners and operators of Teledyne Continental Motors (TCM) IO-360, TSIO-360, LTSIO-360, O-470, IO-470, TSIO-470, IO-520, TSIO-520, LTSIO-520, IO-550, TSIO-550, and TSIOL-550 series reciprocating engines by individual letters. This amendment requires removing a core sample of material from the propeller mounting flange of certain crankshafts, and sending the core sample to TCM for evaluation. This amendment is prompted by reports of crankshaft failures, and by the addition of additional crankshaft serial numbers (SN) that have been added to the suspect population. The actions specified by this AD are intended to prevent fracture of the crankshaft connecting rod journal, which could result in total engine power loss, in-flight engine failure and possible forced landing.