Results
99-15-04: This amendment adopts a new airworthiness directive (AD) that applies to all The New Piper Aircraft, Inc. (Piper) Models PA-46-310P and PA-46-350P airplanes. This AD requires calibrating the turbine inlet temperature system to assure the accuracy of the existing turbine inlet temperature indicator and wiring for all of the applicable airplanes, and repairing or replacing any turbine inlet temperature system that fails the calibration test. This AD also requires repetitively replacing the turbine inlet temperature probe on the Model PA-46-350P airplanes, and inserting a copy of this AD into the Pilot s Operating Handbook of certain airplanes. This AD is the result of field reports that indicate service accuracy problems with the existing turbine inlet temperature system. The actions specified by this AD are intended to prevent improper engine operation caused by improperly calibrated turbine inlet temperature indicators or defective turbine inlet temperature probes, whichcould result in engine damage/failure with consequent loss of control of the airplane.
2021-23-21: The FAA is adopting a new airworthiness directive (AD) for certain The Boeing Company Model 787-8 and 787-9 airplanes. This AD was prompted by reports that shimming requirements were not met during the assembly of certain structural joints, which can result in reduced fatigue thresholds and cracking of the affected structural joints. This AD requires repetitive inspections for cracking of certain areas of the aft wheel well bulkhead (AWWB) body chord and AWWB side fitting and failsafe straps, and repair of any cracking found. The FAA is issuing this AD to address the unsafe condition on these products.
2007-04-21: The FAA is adopting a new airworthiness directive (AD) for all Fokker Model F.28 Mark 0070 and 0100 airplanes. This AD requires a one- time inspection of the fuel lines located in the left and right main landing gear (MLG) bays to determine the clearance between the fuel and hydraulic lines. If necessary, this AD also requires an inspection of fuel lines for chafing, the replacement of a chafed fuel line with a new fuel line, and the repositioning of existing clamps and installation of additional clamps between the fuel and hydraulic lines. This AD results from a fuel leak found in the left MLG bay. We are issuing this AD to detect and correct inadequate clearance between fuel and hydraulic lines in the MLG bay, which could lead to chafing of a fuel line and fuel leakage. A fuel leak near hot brakes could result in a fire in the MLG bay.
2000-19-10: This amendment supersedes an existing airworthiness directive (AD), applicable to all EMBRAER Model EMB-120 series airplanes, that currently requires a one-time inspection of the movable backstop of the elevator pitch trim command system to ensure that it is installed correctly, and corrective action, if necessary. That AD also requires installation of a guide to maintain the movable backstop in its correct position. This amendment adds a requirement for an additional one- time inspection. 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 a sudden change in pitch attitude caused by autopilot disconnect, which could result in reduced controllability of the airplane.
99-08-16: This amendment adopts a new airworthiness directive (AD), that requires revisions to the Engine Time Limits section in the Engine Shop Manual (ESM) for CFM International (CFMI) CFM56-2, -2A, -2B, -3, -3B, and -3C series turbofan engines to include required enhanced inspection of selected critical life-limited parts at each piece-part exposure. This amendment will also require an air carrier's approved continuous airworthiness maintenance program to incorporate these inspection procedures. This amendment is prompted by a Federal Aviation Administration (FAA) study of in-service events involving uncontained failures of critical rotating engine parts which indicated the need for improved inspections. The improved inspections are needed to identify those critical rotating parts with conditions, that if allowed to continue in service, could result in uncontained failures. The actions specified by this AD are intended to prevent critical life-limited rotating engine part failure, which could result in an uncontained engine failure and damage to the airplane.
2018-21-14: We are adopting a new airworthiness directive (AD) for certain Zodiac Aerotechnics (Zodiac) oxygen mask regulators. This AD was prompted by reports that certain silicon harness inflation hoses installed on certain flight crew quick donning mask harnesses have shown an unusually high premature rupture rate. This AD requires inspection and replacement of certain oxygen mask regulator harness inflation hoses. We are issuing this AD to address the unsafe condition on these products.
2000-17-52: This document publishes in the Federal Register an amendment adopting Airworthiness Directive (AD) 2000-17-52, which was sent previously to all known U.S. owners and operators of Agusta S.p.A. (Agusta) Model A109E helicopters by individual letters. This AD requires, before further flight, visually inspecting any main rotor rotating scissors assembly for correct installation and replacing any unairworthy part with an airworthy part. If the rotating scissors attachment bolt (attachment bolt) is not replaced with a new part at the initial inspection, this AD also requires removing the rotating scissors assembly to inspect the attachment bolt for a crack and replacing any cracked attachment bolt with a new attachment bolt before further flight. This amendment is prompted by two incidents of flight control malfunctions. The actions specified by this AD are intended to prevent failure of the rotating scissors assembly and subsequent loss of control of the helicopter.
2019-01-04: We are adopting a new airworthiness directive (AD) for all The Boeing Company Model 787 series airplanes. This AD was prompted by a report of an uncommanded descent and turn that occurred after an inflight switch to the spare flight management function (FMF). This AD requires an inspection of the flight management system (FMS) to determine if certain operational program software (OPS) is installed and installation of new FMS OPS and a software check if necessary. For certain airplanes, this AD also requires concurrent actions. We are issuing this AD to address the unsafe condition on these products.
2019-03-01: We are adopting a new airworthiness directive (AD) for certain Pratt & Whitney Division (PW) PW4074, PW4074D, PW4077, PW4077D, PW4084D, PW4090, and PW4090-3 turbofan engines. This AD was prompted by an in-flight failure of a 1st-stage low-pressure compressor (LPC) blade. This AD requires initial and repetitive thermal acoustic imaging (TAI) inspections for cracks in certain 1st-stage LPC blades and removal of those blades that fail inspection. We are issuing this AD to address the unsafe condition on these products.
2000-19-05: This amendment supersedes an existing airworthiness directive (AD); applicable to certain Boeing Model 737-100, -200, -200C, -300, -400, and -500 series airplanes; that currently requires a one-time inspection of the attachment nuts at each end attachment of the elevator tab push rods to measure run-on torque values, and corrective actions, if necessary. This amendment adds a requirement to replace all existing bolts and attachment nuts at the forward and aft end attachment of each elevator tab push rod with new bolts and self-locking castellated nuts with cotter pins. This amendment is prompted by reports of excessive high-frequency airframe vibration during flight, with consequent structural damage to the elevator tab, elevator, and stabilizer. The actions specified by this AD are intended to prevent detachment of an elevator tab push rod due to a detached nut at either end attachment of a push rod, which could result in excessive high-frequency airframe vibration during flight; consequent structural damage to the elevator tab, elevator, and horizontal stabilizer; and reduced controllability of the airplane.
2000-23-07: This amendment supersedes an existing airworthiness directive (AD), applicable to certain Airbus Model A300 and all Model A300-600 and A310 series airplanes, that currently requires performing a pitch trim system test to detect any continuity defect in the autotrim function, and follow-on corrective actions, if necessary. This amendment requires repetitive inspections of the autotrim function to detect such defects, and corrective actions, if necessary. This amendment also expands the applicability to include additional airplanes. 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 a sudden change in pitch due to an out-of-trim condition combined with an autopilot disconnect, which could result in reduced controllability of the airplane.
2007-04-23: The FAA is superseding an existing airworthiness directive (AD), which applies to certain Fokker Model F.28 Mark 0070 and 0100 airplanes. That AD currently requires a one-time inspection of the sliding members in the main landing gear (MLG) for cracking and replacement of the sliding members with serviceable parts if necessary. This new AD adds repetitive magnetic particle inspections of the sliding members of the MLG for cracking and corrective actions as necessary. This AD results from inspection findings that have shown repetitive inspections are needed to establish fleet safety. We are issuing this AD to detect and correct fatigue cracking of the sliding member, which could result in possible separation of the MLG from the airplane and consequent reduced controllability of the airplane upon landing and possible injury to passengers.
2007-04-27: The FAA is adopting a new airworthiness directive (AD) for all Fokker Model F.28 Mark 1000, 2000, 3000, and 4000 airplanes. This AD requires a one-time inspection of the left- and right-hand main landing gear (MLG) downlock actuators or a review of the airplane maintenance records to determine the part number of each downlock actuator installed, and replacement of identified MLG downlock actuators with modified MLG downlock actuators. This AD results from a report of a failed downlock actuator, which resulted in the left MLG collapsing during taxi after landing. We are issuing this AD to prevent failure of the downlock actuator, which could prevent the MLG side stay from locking properly, resulting in collapse of the MLG during ground maneuvers or upon landing.
95-24-04: This amendment adopts a new airworthiness directive (AD), applicable to all Airbus Model A300 and A300-600 series airplanes, that requires repetitive eddy current inspections to detect cracks at the aft spar web of the wings, and repair, if necessary. This amendment is prompted by reports indicating that cracks have been found in the rear spar web of the wings between ribs 1 and 2 of an in-service airplane and during testing on the fatigue test wing; the cracking occurred due to fatigue-related high shear stress. The actions specified by this AD are intended to prevent such fatigue-related cracking, which could result in reduced structural integrity of the wing.
2019-01-07: We are adopting a new airworthiness directive (AD) for certain Airbus SAS Model A321-111, -112, -131, -211, -212, -213, -231, and -232 airplanes. This AD was prompted by a report that during removal of left-hand (LH) gear rib 5, four failed fasteners were discovered. This AD requires a one-time ultrasonic inspection of the LH and right-hand (RH) wing rib 5-to-rear spar attachments for cracked or failed fasteners, and if necessary, a detailed inspection of the gear rib 5 and spar web for cracks and damage; a rotating probe test of the gear rib and spar web bolt holes for cracks and damage; reaming the gear rib and the spar web bolt holes; and replacement of cracked or failed fasteners. We are issuing this AD to address the unsafe condition on these products.
95-20-02: 95-20-02 AIRBUS INDUSTRIE: Amendment 39-9380. Docket 94-NM-56-AD. Applicability: Model A300-600 series airplanes; having manufacturer's serial numbers (MSN) 252 through 553 inclusive; and on which Airbus Industrie Production Modification No. 07601 has not been accomplished prior to delivery; certificated in any category. NOTE 1: This AD applies to each airplane identified in the preceding applicability provision, regardless of whether it has been modified, altered, or repaired in the area subject to the requirements of this AD. For airplanes that have been modified, altered, or repaired so that the performance of the requirements of this AD is affected, the owner/operator must use the authority provided in paragraph (d) of this AD to request approval from the FAA. This approval may address either no action, if the current configuration eliminates the unsafe condition; or different actions necessary to address the unsafe condition described in this AD. Such a requestshould include an assessment of the effect of the changed configuration on the unsafe condition addressed by this AD. In no case does the presence of any modification, alteration, or repair remove any airplane from the applicability of this AD. Compliance: Required as indicated, unless accomplished previously. To prevent degradation of the structural integrity of the airframe due to cracks in the rear spar, accomplish the following: NOTE 2: Accomplishment of the inspections and repair of cracking in accordance with Airbus Industrie Service Bulletin A300-57-6017, dated November 22, 1993, prior to the effective date of this AD, is acceptable for compliance with the applicable action specified in this amendment. (a) Perform a high frequency eddy current (HFEC) rototest inspection to detect cracks in certain bolt holes where the main landing gear (MLG) forward pick-up fitting and MLG rib 5 aft are attached to the rear spar, in accordance with Airbus Industrie Service Bulletin A300- 57-6017, Revision 1, (includes Appendix 1), dated July 25, 1994. NOTE 3: This service bulletin also references Airbus Industrie Service Bulletin A300- 57-6020, dated November 22, 1993, as an additional source of service information. (1) For airplanes that have accumulated 17,300 total landings or less as of the effective date of this AD: Inspect prior to the accumulation of 17,300 total landings, or within 1,500 landings after the effective date of this AD, whichever occurs later. (2) For airplanes that have accumulated 17,301 or more total landings, but less than 19,300 total landings as of the effective date of this AD: Inspect within 1,500 landings after the effective date of this AD. (3) For airplanes that have accumulated 19,300 or more total landings as of the effective date of this AD: Inspect within 750 landings after the effective date of this AD. (b) If no crack is found during the inspection required by paragraph (a) of this AD, repeat that inspection thereafter at the time specified in either paragraph (b)(1) or (b)(2) of this AD, as applicable. (1) For airplanes on which Airbus Industrie Modification 07716 (as described in Airbus Industrie Service Bulletin A300-57-6020) has not been accomplished, inspect at the time specified in paragraph (b)(1)(i) or (b)(1)(ii) of this AD, as applicable. (i) For airplanes having MSN 465 through 553 inclusive: Repeat the inspection at intervals not to exceed 13,000 landings. (ii) For airplanes having MSN 252 through 464 inclusive: Repeat the inspection at intervals not to exceed 8,400 landings. (2) For airplanes on which Airbus Industrie Modification 07716 has been accomplished, inspect at the time specified in either paragraph (b)(2)(i) or (b)(2)(ii) of this AD, as applicable. (i) For airplanes having MSN 465 through 553 inclusive: Repeat the inspection at intervals not to exceed 11,800 landings. (ii) For airplanes having MSN 252through 464 inclusive: Repeat the inspection within 10,700 landings following the initial inspection required by paragraph (a) of this AD, and thereafter at intervals not to exceed 7,500 landings. (c) If any crack is found during the inspection required by either paragraph (a) or (b) of this AD, prior to further flight, accomplish the requirements of either paragraph (c)(1) or (c)(2) of this AD, as applicable. (1) For airplanes on which Airbus Industrie Modification 07716 has not been accomplished: Oversize the bolt hole by 1/32 inch and repeat the HFEC inspection required by paragraph (a) of this AD, in accordance with Airbus Service Bulletin 300-57-6017, Revision 1, dated July 25, 1994. After accomplishing the oversizing and HFEC inspection, repeat the inspection as required by paragraph (b) of this AD at the applicable schedule specified in that paragraph. (i) If no cracking is detected, install the second oversize bolt in accordance with the service bulletin.(ii) If any cracking is detected, repair in accordance with a method approved by the Manager, Standardization Branch, ANM-113, FAA, Transport Airplane Directorate. (2) For airplanes on which Airbus Industrie Modification 07716 has been accomplished: Repair in accordance with a method approved by the Manager, Standardization Branch, ANM-113. After repair, repeat the inspections as required by paragraph (b) of this AD at the applicable schedule specified in that paragraph. (d) An alternative method of compliance or adjustment of the compliance time that provides an acceptable level of safety may be used if approved by the Manager, Standardization Branch, ANM-113. Operators shall submit their requests through an appropriate FAA Principal Maintenance Inspector, who may add comments and then send it to the Manager, Standardization Branch, ANM-113. NOTE 4: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Standardization Branch, ANM-113. (e) Special flight permits may be issued in accordance with sections 21.197 and 21.199 of the Federal Aviation Regulations (14 CFR 21.197 and 21.199) to operate the airplane to a location where the requirements of this AD can be accomplished. (f) The inspections and installation shall be done in accordance with Airbus Industrie Service Bulletin A300-57-6017, Revision 1, (includes Appendix 1), dated July 25, 1994. This incorporation by reference was approved by the Director of the Federal Register in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. Copies may be obtained from Airbus Industrie, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France. Copies may be inspected at the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington; or at the Office of the Federal Register, 800 North Capitol Street, NW., suite 700, Washington, DC. (g) This amendment becomes effective on November 9, 1995.
96-11-05: This amendment adopts a new airworthiness directive (AD), applicable to certain Airbus Industrie Model A300, A300-600, and A310 series airplanes, that requires inspections to detect cracks in the lower spar axis of the pylons between ribs 6 and 7, and repair, if necessary. This amendment is prompted by reports that fatigue cracking has been found on the lower spar of the pylon. The actions specified by this AD are intended to prevent such fatigue cracking, which could result in reduced structural integrity of the lower spar of the pylon.
2007-04-25: 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 aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as a deficiency in compliance with 14 CFR 23.967(d). There have been instances indicating that production aircraft may not have a metal barrier between the cabin and the fuel tank bay. Lack of a barrier could allow flammable fuel vapors to enter the cabin. We are issuing this AD to require actions to correct the unsafe condition on these products.
2000-19-02: This amendment adopts a new airworthiness directive (AD) that is applicable to all EMBRAER Model EMB-135 and EMB-145 series airplanes. This action requires repetitive inspections of the electrical connectors of the electric fuel pumps to detect discrepancies, and follow- on corrective actions. This action is necessary to prevent failure of the electrical connectors of the fuel pumps, which could result in fuel leakage from the connectors or electrical arcing across the connector pins of the pump, and consequent fuel fire or explosion.
2019-01-06: We are adopting a new airworthiness directive (AD) for all The Boeing Company Model 737-100, -200, -200C, -300, -400, and -500 series airplanes. This AD was prompted by a report of cracks in a certain body station (STA) frame web and doubler at fastener holes common to the stop fitting at a certain stringer. This AD requires repetitive surface high frequency eddy current (HFEC) inspections for cracking of the frame web and doubler at the stop fitting at a certain stringer, and applicable on-condition actions. We are issuing this AD to address the unsafe condition on these products.
T95-18-51: T95-18-51 HAMILTON STANDARD: TELEGRAPHIC AD ISSUED ON AUGUST 25, 1995. DOCKET 95-ANE-48. APPLICABILITY: HAMILTON STANDARD MODELS 14RF-9, 14RF-19, 14RF-21, AND 14SF-5, 14SF-7, 14SF-11, 14SFL11, 14SF-15, 14SF-17, 14SF-19, AND 14SF-23; AND HAMILTON STANDARD/BRITISH AEROSPACE 6/5500/F PROPELLERS INSTALLED ON BUT NOT LIMITED TO EMBRAER EMB-120 AND EMB 120-RT; SAAB-SCANIA SF 340B; AEROSPATIALE ATR42-100, ATR42-300, ATR42-320, ATR72; DEHAVILLAND DHC-8-100 SERIES, DHC-8-300 SERIES; CONSTRUCCIONES AERONAUTICAS SA (CASA) CN-235 SERIES AND CN-235-100; CANADAIR CL-215T AND CL-415; AND BRITISH AEROSPACE ATP AIRPLANES. NOTE: THIS AD APPLIES TO EACH PROPELLER IDENTIFIED IN THE PRECEDING APPLICABILITY PROVISION, REGARDLESS OF WHETHER IT HAS BEEN MODIFIED, ALTERED, OR REPAIRED IN THE AREA SUBJECT TO THE REQUIREMENTS OF THIS AD. FOR PROPELLERS THAT HAVE BEEN MODIFIED, ALTERED, OR REPAIRED SO THAT THE PERFORMANCE OF THE REQUIREMENTS OF THIS AD IS AFFECTED, THE OWNER/OPERATOR MUST USE THE AUTHORITY PROVIDED IN PARAGRAPH (E) TO REQUEST APPROVAL FROM THE FAA. THIS APPROVAL MAY ADDRESS EITHER NO ACTION, IF THE CURRENT CONFIGURATION ELIMINATES THE UNSAFE CONDITION, OR DIFFERENT ACTIONS NECESSARY TO ADDRESS THE UNSAFE CONDITION DESCRIBED IN THIS AD. SUCH A REQUEST SHOULD INCLUDE AN ASSESSMENT OF THE EFFECT OF THE CHANGED CONFIGURATION ON THE UNSAFE CONDITION ADDRESSED BY THIS AD. IN NO CASE DOES THE PRESENCE OF ANY MODIFICATION, ALTERATION, OR REPAIR REMOVE ANY PROPELLER FROM THE APPLICABILITY OF THIS AD. COMPLIANCE: REQUIRED AS INDICATED, UNLESS ACCOMPLISHED PREVIOUSLY. TO PREVENT SEPARATION OF A PROPELLER BLADE DUE TO CRACKS INITIATING IN THE BLADE TAPER BORE, THAT CAN RESULT IN AIRCRAFT DAMAGE, AND POSSIBLE LOSS OF AIRCRAFT CONTROL, ACCOMPLISH THE FOLLOWING: (A) FOR HAMILTON STANDARD 14RF-9 PROPELLER BLADES, INSTALLED ON EMBRAER EMB-120 SERIES AIRCRAFT, WITHIN THE NEXT 10 FLIGHT CYCLES AFTER THE EFFECTIVE DATE OF THIS AD, REMOVE FROM SERVICE PROPELLER BLADES THAT HAVE BEEN ULTRASONICALLY SHEAR WAVE INSPECTED IN ACCORDANCE WITH AD 94-09-06 OR AD 95-05-03, REMOVED FROM SERVICE DUE TO CRACK INDICATIONS, AND SUBSEQUENTLY REWORKED AND RETURNED TO SERVICE. THESE PROPELLER BLADES INCLUDE, BUT ARE NOT LIMITED TO, THE FOLLOWING SERIAL NUMBERS: 847598, 851646, 852085, 852561, 853151, 854530, 854535, 854838, 855014, 855042, 855196, 855859, 857375, 858696, 859824, 860589, 867590, 876707, 880245 (B) FOR HAMILTON STANDARD MODELS 14RF-19, 14RF-21, AND 14SF-5, 14SF-7, 14SF-11, 14SFL11, 14SF-15, 14SF-17, 14SF-19, AND 14SF-23; AND HAMILTON STANDARD/BRITISH AEROSPACE 6/5500/F PROPELLER BLADES, INSTALLED ON AIRCRAFT OTHER THAN EMBRAER EMB-120 AIRCRAFT, WITHIN THE NEXT 10 FLIGHT CYCLES AFTER THE EFFECTIVE DATE OF THIS AD, AND THEREAFTER AT INTERVALS NOT TO EXCEED 1,250 FLIGHT CYCLES SINCE LAST INSPECTION, PERFORM AN ULTRASONIC SHEAR WAVE INSPECTION FOR CRACKS IN THE BLADE TAPER BORE OF PROPELLER BLADES THAT HAVE BEEN ULTRASONICALLY INSPECTED IN ACCORDANCE WITH AD 94-09-06 OR AD 95-05-03, REMOVED FROM SERVICE DUE TO CRACK INDICATIONS, AND SUBSEQUENTLY REWORKED AND RETURNED TO SERVICE. PERFORM THE ULTRASONIC SHEAR WAVE INSPECTION IN ACCORDANCE WITH THE ACCOMPLISHMENT INSTRUCTIONS OF THE FOLLOWING HAMILTON STANDARD ALERT SERVICE BULLETINS (ASB'S), AS APPLICABLE: NO. 14RF-21-61-A68, DATED AUGUST 25, 1995; NO. 14SF-61-A88, DATED AUGUST 25, 1995; NO. 14RF-19-61-A49, DATED AUGUST 25, 1995; NO. 6/5500/F-61-A36, DATED AUGUST 25, 1995. REMOVE CRACKED PROPELLER BLADES FROM SERVICE AND REPLACE WITH SERVICEABLE PARTS. (C) PROPELLER BLADES REMOVED FROM SERVICE IN ACCORDANCE WITH THIS AD MAY NOT BE RETURNED TO SERVICE. (D) FOR THE PURPOSE OF THIS AD, A FLIGHT CYCLE IS DEFINED AS ONE TAKEOFF AND THE NEXT LANDING OF AN AIRCRAFT. (E) AN ALTERNATIVE METHOD OF COMPLIANCE OR ADJUSTMENT OF THE INITIAL COMPLIANCE TIME THAT PROVIDES AN ACCEPTABLE LEVEL OF SAFETY MAY BE USED IF APPROVED BY THE MANAGER, BOSTON AIRCRAFT CERTIFICATION OFFICE. THE REQUEST SHOULD BE FORWARDED THROUGH AN APPROPRIATE FAA PRINCIPAL MAINTENANCE INSPECTOR, WHO MAY ADD COMMENTS AND THEN SEND IT TO THE MANAGER, BOSTON AIRCRAFT CERTIFICATION OFFICE. NOTE: INFORMATION CONCERNING THE EXISTENCE OF APPROVED ALTERNATIVE METHODS OF COMPLIANCE WITH THIS AIRWORTHINESS DIRECTIVE, IF ANY, MAY BE OBTAINED FROM THE BOSTON AIRCRAFT CERTIFICATION OFFICE. (F) SPECIAL FLIGHT PERMITS MAY BE ISSUED IN ACCORDANCE WITH SECTIONS 21.197 AND 21.199 OF THE FEDERAL AVIATION REGULATIONS (14 CFR 21.197 AND 21.199) TO OPERATE THE AIRCRAFT TO A LOCATION WHERE THE REQUIREMENTS OF THIS AD CAN BE ACCOMPLISHED. (G) COPIES OF THE APPLICABLE SERVICE INFORMATION MAY BE OBTAINED FROM HAMILTON STANDARD, ONE HAMILTON ROAD, WINDSOR LOCKS, CT 06096-1010; TELEPHONE (203) 654-3610. THIS INFORMATION MAY BE EXAMINED AT THE FAA, NEW ENGLAND REGION, OFFICE OF THE ASSISTANT CHIEF COUNSEL, 12 NEW ENGLAND EXECUTIVE PARK, BURLINGTON, MA. (H) TELEGRAPHIC AD T95-18-51, ISSUED ONAUGUST 25, 1995, BECOMES EFFECTIVE UPON RECEIPT.
2007-04-26: The FAA is superseding an existing airworthiness directive (AD) for Pratt & Whitney PW4077D, PW4084D, PW4090, and PW4090-3 turbofan engines that were reassembled with previously used high pressure compressor (HPC) exit brush seal packs and new or refurbished HPC exit diffuser air seal lands. That AD currently requires replacing the HPC exit inner and outer brush seal packs with new brush seal packs, or replacing the HPC exit brush seal assembly with a new HPC exit brush seal assembly. This AD requires replacing the HPC exit inner and outer brush seal packs with new brush seal packs, using either original equipment manufactured (OEM) parts, or FAA-approved part manufacturer approval (PMA) parts. This proposed AD also applies to engines reassembled with a PMA HPC exit inner and or outer brush seal packs. This AD results from a request to include PMA HPC exit inner and outer brush seal packs and to include the engines with PMA parts already installed, in the AD. We are issuing this AD to prevent uncontained engine failure, damage to the airplane, and injury to passengers.
2007-04-08: The FAA adopts a new airworthiness directive (AD) for certain EADS SOCATA airplanes. This AD requires you to inspect the pilot door locking stop-fittings for correct length and, if any incorrect length pilot door locking stop-fittings are found, replace them. This AD results from mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for France. We are issuing this AD to detect and replace incorrect length pilot door locking stop- fittings. This condition, if not corrected, could result in depressurization of the airplane.
2018-24-01: We are adopting a new airworthiness directive (AD) for certain International Aero Engines (IAE) PW1100G-JM turbofan engine models with certain low-pressure turbine (LPT) 1st- and 3rd-stage disks installed. This AD was prompted by a report of manufacturing defects found on delivered LPT 1st- and 3rd-stage disks. This AD requires removing the LPT 1st- or 3rd-stage disk from service and replacing with a part eligible for installation. We are issuing this AD to address the unsafe condition on these products.
98-19-22: This amendment adopts a new airworthiness directive (AD), applicable to certain Airbus Model A310 and A300-600, that requires repetitive visual inspections to detect corrosion on the lower rim area of the fuselage rear pressure bulkhead; and follow-on actions, if necessary. 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 detect and correct corrosion at the lower rim area of the fuselage rear pressure bulkhead, which could result in reduced structural integrity of the bulkhead, and consequent decompression of the cabin.