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69-24-01: 69-24-01 AER PEGASO C.A.R.M.A.M.: Amdt. 39-877. Applies to Aer-Pegaso Model M.100S and C.A.R.M.A.M. Model M.200 gliders. Compliance is required within the next 25 hours' time in service after the effective date of this AD, unless already accomplished. To detect improper installation of the horizontal stabilizer to the glider, accomplish the following: (a) Install an inspection window on the left side of the dorsal fin to allow visual confirmation of the elevator "quick disconnect" attachment and paint the two plates of the elevator control transmission fork in accordance with Aer-Pegaso Technical Bulletin N.10/M- 100S, dated September 26, 1969, or an FAA-approved equivalent. (b) Install the following placard in the cockpit in clear view of the pilot: "Before the first flight after rigging the tailplane to the fuselage, look through the inspection window located on the left side of the dorsal fin and visually confirm that the end (ball bearing) of the elevator control lever is correctly engaged in the corresponding fork of the elevator control transmission. To do this, it may be necessary to move the control stick in the longitudinal direction in order to bring the lever end into view through the window. If the rigging is correct, the ball bearing will appear between the fork sides." This amendment becomes effective November 23, 1969.
2002-03-16: This amendment supersedes an existing airworthiness directive (AD) for Model OH-13E, OH-13H, and OH-13S helicopters manufactured by Bell Helicopter Textron, Inc. (BHTI). That AD currently requires either recurring liquid penetrant or eddy current inspections of the main rotor blade grip (grip) threads for a crack. If a crack is detected, that AD requires, before further flight, replacing the cracked grip with an airworthy grip. That AD also establishes a retirement life of 1200 hours time-in-service (TIS) for each grip. This amendment adds two part numbers (P/N) to the applicability and requires only recurring eddy current inspections of the grip threads. This AD also requires reporting any results of the grip inspections to the FAA Rotorcraft Certification Office. This amendment is prompted by the issuance of an AD for the civil BHTI Model 47 helicopters and the results of an accident investigation, an operator survey conducted by a trade association, various comments concerning the subject of the current AD, and a further analysis of field service data related to the BHTI Model 47 helicopters. The actions specified by this AD are intended to prevent failure of a grip, loss of a main rotor blade, and subsequent loss of control of the helicopter.
86-20-10: 86-20-10 ROLLS-ROYCE plc: Amendment 39-5415. Applies to Rolls-Royce Dart Mks., 506, 506F, 510, 510A, 511, 511-7E, 514, 514-7, and 515 turboprop engines. Compliance is required as indicated, unless already accomplished. To prevent cracking of high pressure turbine disks, install new or reworked oversize high pressure nozzle guide vane(s) in accordance with Rolls-Royce Dart (R-R) Service Bulletin (SB) Da72-451, Revision 5, dated June 1982, or FAA approved equivalent, by October 1, 1987. Aircraft may be ferried in accordance with the provisions of FAR 21.197 and 21.199 to a base where the AD can be accomplished. Upon request, an equivalent means of compliance with the requirements of this AD may be approved by the Manager, Engine Certification Office, Aircraft Certification Division, Federal Aviation Administration, New England Region, 12 New England Executive Park, Burlington, Massachusetts 01803. Upon submission of substantiating data by an owner or operator through an FAA maintenance inspector, the Manager, Engine Certification Office, New England Region, may adjust the compliance time specified in this AD. R-R SB Da72-451, Revision 5, dated June 1982, identified and described in this document, is 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 this document from the manufacturer may obtain copies upon request to Rolls-Royce plc - East Kilbride, Attn: Dart Engine Service Manager, Glasgow G74-4PY, Scotland. This document may also be examined at the Office of the Regional Counsel, Federal Aviation Administration, New England Region, 12 New England Executive Park, Burlington, Massachusetts 01803, Room 311, Rules Docket Number 86-ANE-19, between the hours of 8:00 a.m. and 4:30 p.m., Monday through Friday, except Federal holidays. This amendment becomes effective on November 4, 1986.
2003-15-04: This amendment adopts a new airworthiness directive (AD), applicable to all BAE Systems (Operations) Limited (Jetstream) Model 4101 airplanes, that requires inspection of the drive trunnion pins for the main landing gear (MLG) doors to determine the part number of the pins and corrective action if necessary. The actions specified by this AD are intended to prevent failure of the MLG and consequent reduced controllability of the airplane during takeoff or landing.
2002-03-08: This amendment supersedes an existing airworthiness directive (AD), that is applicable to Pratt & Whitney PW4000 series turbofan engines. That AD currently requires revisions to the Time Limits Section of the manufacturer's Engine Manuals (EM's) to include required enhanced inspection of selected critical life-limited parts at each piece-part exposure. This amendment modifies the airworthiness limitations section of the manufacturer's manual and an air carrier's approved continuous airworthiness maintenance program to incorporate additional inspection requirements. An FAA study of in-service events involving uncontained failures of critical rotating engine parts has indicated the need for mandatory inspections. The mandatory inspections are needed to identify those critical rotating parts with conditions, which 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 enginepart failure, which could result in an uncontained engine failure and damage to the airplane.
2015-17-08: We are adopting a new airworthiness directive (AD) for certain Bombardier, Inc. Model DHC-8-400 series airplanes. This AD was prompted by an in-service report of an uncommanded and unannunciated nose wheel steering during airplane pushback from the gate. This AD requires installing new cable assemblies with a pull-down resistor. We are issuing this AD to prevent an uncommanded nose wheel steering during takeoff or landing in the event of an open circuit in the steering system, and possible consequent runway excursion.
85-25-11: 85-25-11 CESSNA: Amendment 39-5234. Applies to Models 425 (Serial Numbers 425-0002 thru 425-0236) and 441 (Serial Numbers 441-0001 thru 441-0354) airplanes certificated in any category. Compliance: Required within the next ten hours time-in-service, unless previously accomplished. To preclude failure of the horizontal stabilizer front spar attachments accomplish the following: (a) Replace left and right horizontal stabilizer front spar attach bolt retaining nuts (Part Number NAS1291-8) in accordance with the instructions contained in Cessna Service Bulletin No. CQB85-25, Revision 1, dated December 16, 1985. Purchase replacement NAS1291-8 nuts exclusively from the Cessna Supply Division after November 22, 1985, per the above Cessna Service Bulletin. (b) Return removed NAS1291-8 nuts to Cessna in accordance with Cessna Service Bulletin No. CQB85-25, Revision 1, dated December 16, 1985. (c) Aircraft may be flown in accordance with FAR 21.197 to a location where this AD can be accomplished. (d) An equivalent method of compliance with this AD may be used when approved by the Manager, Wichita Aircraft Certification Office, Federal Aviation Administration, Central Region, 1801 Airport Road, Room 100, Mid-Continent Airport, Wichita, Kansas 67209. All persons affected by this directive may obtain copies of the document referred to herein upon request to the Cessna Aircraft Company, Customer Services, Post Office Box 1521, Wichita, Kansas 67201 or the FAA, Office of the Regional Counsel, Room 1558, 601 East 12th Street, Kansas City, Missouri 64106. This amendment becomes effective February 12, 1986, as to all persons except those persons to whom it was made immediately effective by priority letter AD 85-25-11, issued December 18, 1985, which contained this amendment.
98-26-03: This amendment adopts a new airworthiness directive (AD), applicable to certain Airbus Model A321 series airplanes. This action requires modification and re-identification of the evacuation slide systems at left- and right-hand emergency exits 2 and 3. 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 the loss of the evacuation slides during flight, which could result in damage to the empennage, or inability of airplane occupants to use certain exit doors during an emergency.
2015-17-12: We are adopting a new airworthiness directive (AD) for certain Cessna Aircraft Company Model 500, 501, 550, 551, S550, 560, and 650 airplanes. This AD was prompted by reports of smoke and/or fire in the tailcone caused by sparking due to excessive wear of the brushes in the air conditioning (A/C) motor. This AD requires inspections to determine if certain A/C compressor motors are installed and to determine the accumulated hours on certain A/C compressor motor assemblies; and repetitive replacement of the brushes in the A/C compressor motor assembly, or, as an option to the brush replacement, deactivation of the A/C system and [[Page 51444]] placard installation; and return of replaced brushes to Cessna. We are issuing this AD to prevent the brushes in the A/C motor from wearing down beyond their limits, which could result in the rivet in the brush contacting the commutator, causing sparks and consequent fire and/or smoke in the tailcone with no means to detect or extinguish the fire and/or smoke.
89-08-06: 89-08-06 CALIFORNIA DEPARTMENT OF FORESTRY; GARLICK HELICOPTERS: HAWKINS AND POWERS AVIATION, INC.; HERCULES; INTERNATIONAL HELICOPTERS, INC.; OREGON HELICOPTERS; PILOT PERSONNEL INTERNATIONAL, INC.; SMITH HELICOPTERS; SOUTHERN AERO CORPORATION; AND WEST COAST FABRICATIONS (these helicopters were manufactured by Bell Helicopter Textron, Inc., under military contract): Amendment 39-6464. Docket No. 89-ASW-13. Final copy of Priority Letter AD. Applicability: Model UH-1A, UH-1B, UH-1E, UH-1F, UH-1L, and TH-1L helicopters, certificated in any category, with main transmission spiral bevel gear, P/N 204-040-701-103 installed, having less than 250 hours' time in service after the effective date of this AD and delivered as spares or in a new transmission between January 1, 1988, and April 4, 1989. The spare (uninstalled) spiral bevel gears, P/N 204-040-701-103, affected serial numbers are as follows: A-3819 A-3821 A-3825 A-3826 A-3829 A-3833 A-3834 A-3836 A-3838 A-3840 A-3845 A-3847 A-3848 A-3850 A-3855 A-3856 A-3857 A-3858 A-3861 A-3878 A-3880 A-3885 A-3886 A-3889 A-3891 A-3892 A-3893 A-3895 A-3896 A-3897 A-3899 A-3901 A-3911 A-3915 A-3916 A-3919 A-3920 A-4008 A-4014 A-4017 A-4019 A-4020 A-4021 A-4027 A-4029 A-4068 A-4069 A-4071 A-4075 A-4077 A-4078 A-4079 A-4080 A-4081 A-4083 A-4084 A-4085 A-4087 A-4089 A-4090 A-4091 A-4092 A-4093 A-4094 A-4095 A-4096 A-4097 A-4098 A-4107 A-4108 A-4109 A-4147 A-4184 A-4186 A-4187 A-4188 A-4191 A-4192 A-4193 A-4213 A-4229 A-4233 A-4235 A-4236 A-4241 A-4243 A-4244 A-4245 A-4254 A-4266 A-4267 A-4274 A-4275 A-4280 A-4282 A-4288 A-4289 A-4290 A-4303 A-4319 A-4320 A-4325 A-4327 A-4328 A-4329 A-4332 A-4333 A-4334 A-4335 A-4336 A-4337 A-4358 A-4366 A-4368 A-4369 A-4370 A-4371 A-4372 A-4374 A-4376 A-4377 A-4378 A-4379 A-4380 A-4383 A-4385 A-4386 A-4387 A-4394 A-4395 A-4397 A-4400 A-4401 A-4403 A-4411 A-4417 A-4418 A-4428 Compliance: Required as indicated, unless already accomplished. To prevent failure of the main transmission spiral bevel gear which could result in possible loss of the helicopter, accomplish the following: (a) Within the next 10 hours' time in service after the effective date of this AD and, thereafter before the first flight of each day, accomplish the following: (1) Remove and inspect the transmission internal sump oil filter for evidence of metal contamination (e.g., steel particles in splinter, granular, or flake form). (2) If metal contamination is evident, disassemble the main transmission to determine the extent of damage and replace any unserviceable parts with serviceable parts before further flight. (b) Within the next 10 hours' time in service after the effective date of this AD and, thereafter, at intervals not to exceed 50 hours' time in service from the last inspection, accomplish the following: (1) Remove a quill pad cover, P/N 204-040-174-001, or rotor brake quill from the transmission main ring gear case to gain access to the main transmission spiral bevel gear. (2) Utilizing a bright light and a dental mirror, inspect all teeth in the spiral bevel gear, P/N 204-040-701-103, for evidence of cracks, chipping, and metal deformation. If cracks, chipping, or metal deformation is evident, the part must be removed from service and replaced with a serviceable part before further flight. (3) Reinstall pad cover, P/N 204-040-174-001, or rotor brake quill whichever is applicable. (c) The provisions of this AD do not apply when the time in service of the spiral bevel gear, P/N 204-040-701-103, reaches or exceeds 250 hours' time in service. NOTE: Spiral bevel gear, P/N 204-040-701-103, affected by this AD may be returned to Bell Helicopter Textron, Inc., Attn: CPR Monitor, 3000 South Norwood & Trinity Boulevard, Hurst, Texas 76053, for inspection and reidentification. After reidentification, the provisions of this AD no longer apply. (d) An alternate method of compliance or adjustment of the compliance time, which provides an equivalent level of safety, may be used when approved by the Manager, Rotorcraft Certification Office, Rotorcraft Directorate, Aircraft Certification Service, FAA, Southwest Region, Fort Worth, Texas. (e) In accordance with FAR Sections 21.197 and 21.199, flight is permitted to a base where the inspection requirements of this AD may be accomplished. This amendment (39-6464, AD 89-08-06) becomes effective on February 7, 1990, as to all persons except those persons to whom it was made immediately effective by Priority Letter AD 89-08-06, issued April 12, 1989, which contained this amendment.
87-22-04: 87-22-04 BRITISH AEROSPACE: Amendment 39-5750. Applies to Viscount Model 700 series and 800 series airplanes, certificated in any category. Compliance is required as indicated, unless previously accomplished. To prevent failure of landing gear ram feet, accomplish the following: A. For all Model 700 series airplanes, pre-modification D2781: 1. Within 30 days or 120 landings after the effective date of this AD, whichever occurs first, inspect and replace, if necessary, main landing gear ram feet in accordance with Paragraph 2.0, "Accomplishment Instructions," of British Aerospace (BAe) Viscount Preliminary Technical Leaflet (PTL) No. 317, dated June 10, 1986. 2. Repeat the above inspection at intervals not to exceed 14 months or 1,600 landings, whichever occurs first. B. For all Model 800 series airplane, pre-modification F1323: 1. Within 30 days or 120 landings after the effective date of this AD, whichever occurs first, inspect and replace, if necessary, main landing gear ram feet in accordance with Paragraph 2.0, "Accomplishment Instructions," of BAe Viscount PTL No. 186, dated June 10, 1986. 2. Repeat the above inspection at intervals not to exceed 14 months or 1,600 landings, whichever occurs first. C. An 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, Standardization Branch, ANM-113, FAA, Northwest Mountain Region. D. 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 inspections required by this AD. All persons affected by this directive who have not already received the appropriate service document from the manufacturer may obtain copies upon request to British Aerospace, Inc., Librarian for Service Bulletins, P.O. Box 17414, Dulles International Airport, Washington, D.C. 20041. This document 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 becomes effective November 13, 1987.
2025-03-08: The FAA is adopting a new airworthiness directive (AD) for all Airbus SAS Model A318, A319, A320, and A321 series airplanes; Model A330-200, -200 Freighter, -300, -800, and -900 series airplanes; and Model A340-200, -300, -500, and -600 series airplanes. This AD was prompted by reports of trimmable horizontal stabilizer actuators (THSAs) being delivered to operators having erroneous information (accumulated life) in the authorized release certificate. This AD requires contacting Collins Aerospace for amended authorized release certificates for the affected parts and replacing the affected parts if necessary, and prohibits the installation of affected parts, 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.
2002-03-11: This amendment supersedes an existing airworthiness directive (AD), applicable to certain Airbus Model A319, A320, and A321 series airplanes, that currently requires a one-time ultrasonic inspection to detect disbonding of the skin attachments at the stringers and spars of the vertical stabilizer, repair, if necessary, and, for certain airplanes, prior or concurrent modification of the vertical stabilizer to ensure proper reinforcement of its attachment to the skin. This amendment adds repetitive ultrasonic inspections of the subject area, and repair, if necessary. It also adds installation of fasteners to reinforce the bonds to the skin, which terminates the repetitive inspections. 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 failure of the bonds of the vertical stabilizer spar boxes to the skin, which could lead to reduced structural integrity of the spar boxes.
2000-07-04: This amendment adopts a new airworthiness directive (AD), applicable to certain Dornier Model 328-100 series airplanes, that requires repetitive tests of the flight idle backup system of the propeller control system; repetitive inspections to determine the level of wear of the pins and bushings of the cam followers on the power lever rods of the engine controls; and follow-on corrective actions, if necessary. This amendment also requires eventual replacement of the power lever and condition lever rods of the engine controls with new, improved parts, which constitutes terminating action for the repetitive tests and inspections. 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 failure of the flight idle backup system. In the event of failure of the primary propeller control system, such failure of the flight idle backup system could lead to uncommanded movement of the pitch of the propeller blade to below flight idle and into reverse thrust during flight, and consequent reduced controllability of the airplane.
2020-26-08: The FAA is adopting a new airworthiness directive (AD) for The Boeing Company Model 787-8, 787-9, and 787-10 airplanes powered by Rolls Royce Trent 1000 engines. This AD was prompted by reports of damage to the inner fixed structure (IFS) forward upper fire seal and damage to thermal insulation blankets in the forward upper area of the thrust reverser (TR). This AD requires repetitive inspections of the IFS forward upper fire seal and thermal insulation blankets in the forward upper area of the TR for damage and applicable on-condition actions. The FAA is issuing this AD to address the unsafe condition on these products.
2003-14-12: This amendment adopts a new airworthiness directive (AD) for the specified Eurocopter France (ECF) model helicopters that requires determining whether specified main or tail rotor (rotor) parts are installed and, if so, updating and recording the correct hours time-in- service (TIS) or cycles of each part. If the hours TIS or cycles of any rotor part exceed its life limit, this AD also requires replacing that part with an airworthy part within 50 hours TIS. This amendment is prompted by the need to correct the Equipment Log Card (FME) to accurately reflect the total hours TIS and cycles of certain repaired or overhauled rotor parts. The actions specified by this AD are intended to prevent failure of a life limited rotor part, loss of a rotor, and subsequent loss of control of the helicopter.
2015-17-11: We are adopting a new airworthiness directive (AD) for Airbus Helicopters Model AS350B, AS350BA, AS350B1, AS350B2, AS350B3, AS350C, AS350D, AS350D1, AS355E, AS355F, AS355F1, AS355F2, AS355N, AS355NP, EC130B4, and EC130T2 helicopters. This AD requires inspecting the swashplate assembly rotating star to determine whether a ferrule was installed. If a ferrule exists, this AD requires inspecting the rotating star for a crack and removing any cracked rotating star. This AD was prompted by a report that reconditioning the rotating swashplate per a certain repair procedure could result in the rotating star cracking. The actions of this AD are intended to detect a crack in the rotating star and prevent failure of the rotating star and subsequent loss of control of the helicopter.
87-22-06: 87-22-06 BOEING: Amendment 39-5743. Applies to Model 727 series airplanes, as listed in Boeing Service Bulletin 727-32-267, Revision 1, dated June 15, 1984, certificated in any category. Compliance is required within the next 4,500 hours time-in-service or 2 years after the effective date of this AD, whichever occurs first, unless previously accomplished. \n\n\tTo prevent the main landing gear door release lever from moving to the door open position during flight, accomplish the following: \n\n\tA.\tModify the left and right main landing gear door release levers in accordance with the Accomplishment Instructions of Boeing Service Bulletin 727-32-267, Revision 1, dated June 15, 1984, or later FAA-approved revision. \n\n\tB.\tAn 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, Seattle 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 the Boeing Commercial Airplane Company, P.O. Box 3707, Seattle, Washington 98124. These documents may be examined at 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 becomes effective November 20, 1987.
99-11-04: This document publishes in the Federal Register an amendment adopting Airworthiness Directive (AD) 99-11-04 which was sent previously to all known U.S. owners and operators of Sikorsky Aircraft Model S-76A helicopters by individual letters. This AD requires, before further flight, either revising the flight manual to show reduced single-engine rotorcraft performance or determining if an AC generator interlock system is installed. If an interlock system is installed, the flight manual revision is not required. This amendment is prompted by the discovery that Sikorsky Aircraft Model S-76A helicopters with Turbomeca Arriel 1S1 engines may fail to achieve the specified single-engine rotorcraft performance if an AC generator interlock system is not installed. The actions specified by this AD are intended to prevent the inability of the rotorcraft to achieve certain published one-engine-inoperative performance.
2025-02-09: The FAA is adopting a new airworthiness directive (AD) for all Embraer S.A. Model EMB-120, -120ER, -120FC, -120QC, and -120RT airplanes. This AD was prompted by a structural assessment, which found that the fuselage longitudinal skin splice and panel between certain frames are susceptible to cracking. This AD requires performing repetitive inspections of the fuselage center I longitudinal skin splice and applicable corrective actions, as specified in an Ag[ecirc]ncia Nacional de Avia[ccedil][atilde]o Civil (ANAC) AD, which is incorporated by reference (IBR). The FAA is issuing this AD to address the unsafe condition on these products.
2015-17-01: We are superseding Airworthiness Directive (AD) 2013-21-01 for Eurocopter France Model AS350B, AS350BA, AS350B1, AS350B2, AS350B3, AS350C, AS350D, AS350D1, AS355E, AS355F, AS355F1, AS355F2, AS355N, and AS355NP helicopters. AD 2013-21-01 required certain inspections of each tail rotor pitch horn assembly (pitch horn) for a crack, replacing a cracked pitch horn before further flight, and a one-time visual inspection of pitch horns above certain hours time-in-service (TIS). This new AD retains the requirements of AD 2013-21-01 but requires a repetitive visual inspection for all pitch horns regardless of hours TIS. This AD was prompted by a report of a crack in the yoke of a pitch horn and is intended to detect a crack in the pitch horn to prevent failure of the pitch horn, loss of the anti-torque function, and subsequent loss of control of the helicopter.
98-21-04: This amendment supersedes an existing airworthiness directive (AD), applicable to all Dornier Model 328-100 series airplanes, that currently requires repetitive visual inspections for signs of fuel leakage on the outer wing beginning with Rib 21 and continuing outward; and corrective action, if necessary. This amendment adds a requirement for modification of the lower panels of the outer wing area, which terminates the repetitive inspection requirements. This action also limits the applicability of the existing AD. 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 fuel leakage on the outboard wing, which could result in a fuel explosion and fire.
2001-20-01: This amendment adopts a new airworthiness directive (AD), applicable to Pratt & Whitney Canada (PWC) PT6A-25C and -114A turboprop engines. This amendment will require initial and repetitive visual inspections, and eventual replacement of the compressor bleed valve assembly, with a redesigned valve assembly for -114A and -25C engines. This amendment is prompted by reports of two occurrences of uncommanded engine power loss. The actions specified by this AD are intended to detect wear in the compressor bleed valve assembly which may cause valve orifice blockage, resulting in a loss of power, an inability to accelerate the engine, and an in-flight shutdown.
2015-17-06: We are adopting a new airworthiness directive (AD) for certain Airbus Model A319, A320, and A321 series airplanes. This AD was prompted by reports that on airplanes equipped [[Page 50552]] with sharklets, discretes (used to activate the load alleviation function) are connected on various flight computers using the same ground point. In these cases, the ground point segregation is no longer effective, and a single failure could lead to loss of sharklet identification by flight computers causing a return to the wing tip fence (no sharklet configuration) performance. This AD requires modification of the sharklet ground connection. We are issuing this AD to prevent loss of sharklet identification by the flight computers and subsequent reduced control of the airplane.
2015-16-07: We are adopting a new airworthiness directive (AD) for REIMS AVIATION S.A. Model F406 airplanes. This AD results from mandatory continuing airworthiness information (MCAI) issued by the aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as detachment of the pilot's rudder control pedal in flight. We are issuing this AD to require actions to address the unsafe condition on these products.