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93-16-05: 93-16-05 SHORT BROTHERS, PLC: Amendment 39-8662. Docket 93-NM-12-AD. Applicability: All Model SD3-60 series airplanes, certificated in any category. Compliance: Required as indicated, unless accomplished previously. To prevent reduced structural integrity of the attachment of the horizontal stabilizer to the airplane, accomplish the following: (a) Prior to the accumulation of 20,000 total landings on the horizontal stabilizer or within 3 months after the effective date of this AD, whichever occurs later, and thereafter at intervals not to exceed 4,000 landings, perform an ultrasonic inspection to detect cracking in the attachment lugs of the horizontal stabilizer in accordance with Shorts Service Bulletin SD360-55-19, dated January 18, 1993. If any cracked lug is found, prior to further flight, replace the lug with a serviceable part in accordance with the service bulletin and continue to inspect at intervals not to exceed 4,000 landings in accordance with this paragraph. (b) 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, FAA, Transport Airplane Directorate. 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: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Standardization Branch, ANM-113. (c) Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate the airplane to a location where the requirements of this AD can be accomplished. (d) The inspections and replacement shall be done in accordance with Shorts Service Bulletin SD360-55-19, dated January 18, 1993. 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 Short Brothers, PLC, 2011 Crystal Drive, Suite 713, Arlington, Virginia 22202-3719. 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. (e) This amendment becomes effective on October 4, 1993.
2022-25-12: The FAA is adopting a new airworthiness directive (AD) for all Airbus SAS Model A310 series airplanes. This AD was prompted by a determination that new or more restrictive maintenance requirements and 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.
2001-15-12: This amendment supersedes two airworthiness directives (AD's), 2000-22-01 and 2001-09-07, that both apply to Pratt and Whitney (PW) model PW4000 series turbofan engines. AD 2000-22-01 requires that operators limit the number of PW4000 engines equipped with the high pressure compressors (HPC) in the cutback stator (CBS) configuration to no more than one engine on each airplane, and prohibits the installation of engines with HPC modules in the CBS configuration after the effective date of that AD. AD 2001-09-07 requires that operators limit the number of engines with potentially reduced stability to no more than one engine on each airplane, and remove those engines before exceeding certain cyclic limits. Reports of HPC surges in PW4000 engines that have the HPC in the CBS configuration prompted those AD's. This Amendment will limit the number of PW4000 engines with potentially reduced stability on each airplane by applying rules based on airplane and engine configuration, and require that engines that exceed HPC compressor cyclic limits based on cycles-since-overhaul (CSO) are removed from service. This AD will also limit the number of engines with HPC CBS configuration to one on each airplane, and will establish a minimum rebuild standard for engines that are returned to service. This Amendment is prompted by further analyses of compressor surges in PW4000 engines. The actions specified by this AD are intended to prevent multiple-engine power losses due to high pressure compressor (HPC) surge and to reduce the rate of single-engine surge events.
2001-14-22: This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 747-100 and -200 series airplanes, that requires repetitive inspections for cracking of the station 800 frame assembly, and repair, if necessary. The actions specified by this AD are intended to find and fix fatigue cracks that could extend and fully sever the frame, which could result in development of skin cracks that could lead to rapid depressurization of the airplane. This action is intended to address the identified unsafe condition.
75-22-12: 75-22-12 SIKORSKY: Amendment 39-2400. Applies to Sikorsky model S-55 series helicopters incorporating AiResearch model TSE331-3U-303N engines per Supplemental Type Certificate (STC) SH125WE or SH127WE, certificated in all categories. Compliance required as indicated. To prevent possible inflight power loss accomplish the following: A. Within the next 10 hours time in service after the effective date of this AD, unless already accomplished, and thereafter as required by subparagraph (8): (1) Inspect and functionally test the fuel deceleration valve (AiResearch P/N 692545-400 or 868558-1) by disconnecting the fuel bypass line and capping off the line to prevent fuel leakage from the fuel pump. With the engine operating and the "AIR-GROUND" switch in the "GROUND" position, the deceleration bleed valve is to be cycled electrically open and closed using the decel button on the pilot's cyclic control stick to assure that no fuel leakage occurs when the valve is inthe normally closed position. Replace the valve if it does not function properly or leaks any fuel when closed. Remove cap and reconnect bypass line. (2) Remove the tee fitting (AiRearch P/N 3101322-1) from the engine and visually inspect the orifice for blockage. Replace tee fitting if the orifice is restricted. Reinstall tee fitting to engine if found free of obstructions. (3) With the engine operating at 100 percent engine speed and the "AIR- GROUND" switch in the "AIR" position, functionally test the manual fuel flow control valve (AiResearch P/N 868558-2) for proper operation by cycling this valve using the cyclic control switch. If the engine does not react normally by losing RPM and then recovering to 100 percent engine speed as the manual fuel flow control valve is closed and opened, remove and replace this valve and repeat this functional check. (4) Visually inspect the wiring and electrical connections associated with the deceleration control switch toassure that there has been no chafing or other damage which could cause improper operation of the deceleration bleed valve or manual fuel flow control valve. (5) Calibrate engine tachometer and engine tachometer generator as a pair against an accurate standard to within plus or minus 0.5% true reading. (6) Inspect and adjust, as necessary, the underspeed governor adjustment in accordance with the FAA approved rotorcraft maintenance manual. (7) Inspect and adjust, as necessary, the throttle linkage to insure that the throttle high RPM stop is set correctly with respect to the engine fuel control stop in accordance with the FAA approved rotorcraft maintenance manual. (8) Repeat the calibrations and inspections of paragraphs (5), (6) and (7), above, at intervals not to exceed 500 hours time in service, or twelve months, whichever occurs earlier. The calibrations required in (5) must be repeated whenever a tachometer indicator or tachometer generator is replaced.B. Within the next 10 hours time in service after the effective date of this AD, unless already accomplished: (1) Install the fuel enrichment valve system per AiResearch Service Bulletin TSE331-73-0045, dated August 25, 1975, or later FAA approved revisions, and Helitec Corporation Service Bulletin No. AS55-01-3, dated August 29, 1975; and (2) Incorporate and comply with Aviation Specialties Company Sikorsky S- 55, S-55B, and S-55C FAA approved Rotorcraft Flight Manual (RFM) revision No. 6, dated August 29, 1975, or later FAA approved revisions. NOTE 1: B(1) and (2) shall be performed simultaneously. NOTE 2: Refer to AiResearch Service Bulletin TSE331-735004 dated July 16, 1973, and Aviation Specialties Service Bulletin AS55-01-1 dated July 6, 1973, for identification and location of related hardware. C. Until the actions required by paragraph B. above are performed, the following operating limitations and flight limitations (Section I, RFM) shall apply. (1) Before each takeoff with the collective full down and the rotor engaged, determine that the engine idles above 100.5% RPM with the high RPM stop. (2) At takeoff power the engine speed must not be below 99% RPM. (3) Avoid rapid collective increases under high power conditions. D. After the effective date of this AD refer to the rotorcraft flight manual for the nominal specific gravity of approved fuel types (see Section II, Specific Gravity). Operating personnel shall assure that the engine fuel control specific gravity adjustment is set properly at all times for the type of fuel being used. E. Equivalent procedures may be approved by the Chief, Aircraft Engineering Division, FAA Western Region, upon submission of adequate substantiating data. F. Aircraft may be flown in accordance with FAR 21.197 to a base for performance of the inspections, maintenance, and modifications required by this AD, provided the operating limitations set forth in paragraph (c) are applied. This amendment becomes effective October 31, 1975 for all persons except those to whom it was made effective by individual airmail letters, dated September 8, 1975 which contained this amendment.
93-17-05: 93-17-05 AIRBUS INDUSTRIE: Amendment 39-8676. Docket 93-NM-35-AD. Applicability: Model A320 series airplanes; manufacturer's serial number (MSN) 005 through 012 inclusive, and MSN's 013 through 024 inclusive; certificated in any category. Compliance: Required as indicated, unless accomplished previously. To prevent reduced structural integrity of the fuselage, accomplish the following: (a) Modify the web installation between frames 1 and 2 in accordance with Airbus Industrie Service Bulletin No. A320-53-1002, Revision 1, dated November 30, 1992, at the applicable time specified in paragraph (a)(1) or (a)(2) of this AD. (1) For airplanes having MSN's 005 through 012, inclusive: Within 12,000 landings after the effective date of this AD. (2) For airplanes having MSN's 013 through 024, inclusive: Within 15,000 landings after the effective date of this AD. (b) 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, FAA, Transport Airplane Directorate. 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: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Standardization Branch, ANM-113. (c) Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate the airplane to a location where the requirements of this AD can be accomplished. (d) The modification shall be done in accordance with Airbus Industrie Service Bulletin No. A320-53-1002, Revision 1, dated November 30, 1992, which contains the following list of effective pages: Page Number Revision Level Shown on Page Date Shown on Page 1, 5-6, 10-12, 14, 20, 25-26 1 November 30, 1992 2-4, 7-9, 13, 15-19, 21-24 Original January 17, 1992 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. (e) This amendment becomes effective on October 7, 1993.
2016-22-16: We are adopting a new airworthiness directive (AD) for certain Bombardier, Inc. Model CL-600-2C10 (Regional Jet Series 700, 701, and 702), CL-600-2D15 (Regional Jet Series 705), CL-600-2D24 (Regional Jet Series 900), and CL-600-2E25 (Regional Jet Series 1000) airplanes. This AD was prompted by a determination that wear and possible leakage of the high-pressure seal in the cylinder of the No. 3 hydraulic system reservoir could occur and cause high hydraulic fluid temperature and/or prevent the system from reaching normal operating pressure. This AD requires repetitive operational checks for wear and leakage of the high-pressure seal in the cylinder of the reservoir of the No. 3 hydraulic system, and corrective actions if necessary. We are issuing this AD to address the unsafe condition on these products.
2018-20-13: We are adopting a new airworthiness directive (AD) for all The Boeing Company Model 737 airplanes, excluding Model 737-100, -200, - 200C, -300, -400, and -500 series airplanes; all Model 757-200, -200PF, -200CB, and -300 series airplanes; and all Model 767-200, -300, -300F, and -400ER series airplanes. This AD was prompted by reports of latently failed motor-operated valve (MOV) actuators of the fuel shutoff valves. This AD requires replacing certain MOV actuators of the fuel shutoff valves for the left and right engines (on certain airplanes) and of the auxiliary power unit (APU) fuel shutoff valve (on Model 757 and Model 767 airplanes); and revising the maintenance or inspection program to incorporate certain airworthiness limitations (AWLs). We are issuing this AD to address the unsafe condition on these products.
2010-23-23: This amendment adopts a new airworthiness directive (AD) for the specified ECF model helicopters. This AD results from a mandatory continuing airworthiness information (MCAI) AD issued by the European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Community. The MCAI AD states that EASA received a report of a rear hinged door on a Model AS332L1 helicopter opening in flight without loss of the door. Examinations revealed incorrect positioning of a door catch that resulted in incorrect locking and uncontrolled opening of the door. This condition, if not detected and corrected, can lead to the loss of the hinged door in flight, damage to the main or tail rotor blades, and subsequent loss of control of the helicopter.
91-19-05: 91-19-05 BRITISH AEROSPACE: Amendment 39-8032. Docket No. 91-NM-179-AD. Applicability: Model BAe 125-800A, Model HS.125-700A, and Model DH/BH/HS 125 series airplanes retrofitted with Garrett engines which are pre-mod 253274A; certificated in any category. Compliance: Required as indicated, unless previously accomplished. To prevent the loss of fire extinguishment capability, accomplish the following: (a) Within 30 days after the effective date of this AD, perform a visual inspection of the engine fire extinguisher system wiring to detect crossed wiring, improperly identified or unidentified wiring and wiring supports, missing wiring supports, and loose or improperly locked electrical connectors, in accordance with British Aerospace Service Bulletin 26-31, dated February 25, 1991. (b) If any discrepancy is found during the inspection required by paragraph (a) of this AD, prior to further flight, correct it in accordance with the instructions in British Aerospace Service Bulletin 26-31, dated February 25, 1991. (c) An alternative method 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, Transport Airplane Directorate. NOTE: The request should be forwarded through an FAA Principal Maintenance Inspector, who may concur or comment and then send it to the Manager, Standardization Branch, ANM-113. (d) 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. (e) The inspection and correction requirements shall be done in accordance with British Aerospace Service Bulletin 26-31, dated February 25, 1991. 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 British Aerospace, PLC, Librarian for Service Bulletins, P.O. Box 17414, Dulles International Airport, Washington, D.C. 20041-0414. Copies may be inspected at the FAA, Transport Airplane Directorate, Renton, Washington; or at the Office of the Federal Register, 1100 L Street N.W., Room 8401, Washington, D.C. This amendment (39-8032, AD 91-19-05) becomes effective on September 26, 1991.
2001-15-09: This amendment adopts a new airworthiness directive (AD), applicable to certain Aerospatiale Model ATR42-200, -300, -320, and -500 series airplanes; and Model ATR72 series airplanes; that requires replacement of the existing uplock boxes of the main and nose landing gears with modified uplock boxes. The actions specified by this AD are intended to prevent a mechanical failure of the uplock box mechanisms, which could result in failure of the associated landing gear to extend. This action is intended to address the identified unsafe condition.
2016-22-13: We are adopting a new airworthiness directive (AD) for all The Boeing Company Model 737-600, -700, -700C, -800, -900, and -900ER series airplanes. This AD was prompted by an evaluation by the design approval holder (DAH) indicating that lap splices for certain stringers are subject to widespread fatigue damage (WFD). This AD requires repetitive inspections for cracking in the lower fastener row of the lap splices of certain stringers, and repair if necessary. We are issuing this AD to address the unsafe condition on these products.
90-13-08: 90-13-08 FOKKER: Amendment 39-6632. Docket No. 90-NM-39-AD. Applicability: Model F27 series airplanes, as listed in Fokker Service Bulletin F27/53-109, dated October 10, 1989, certificated in any category. Compliance: Required as indicated, unless previously accomplished. To prevent decompression of the airplane, accomplish the following: A. Perform an inspection of the cockpit window frames, in accordance with Fokker Service Bulletin F27/53-109, dated October 10, 1989, as follows: 1. For Serial Numbers 10561 through 10684, 10686, 10687, 10689 through 10692, prior to the accumulation of 20,000 landings or within 90 days after the effective date of this AD, whichever occurs later. 2. For Serial Numbers 10102 through 10560, prior to the accumulation of 30,000 landings or within 90 days after the effective date of this AD, whichever occur later. B. If cracks are found, repair prior to further flight, in accordance with Fokker Service Bulletin F27/53-110, dated October 27, 1989. 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. NOTE: The request should be forwarded through an FAA Principal Maintenance Inspector (PMI), who will either concur or comment and then send it to the Manager, Standardization Branch, ANM-113. D. 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 Fokker Aircraft USA, Inc., 1199 N. Fairfax Street, Alexandria, Virginia 22314. These documents may be examined at the FAA, Northwest Mountain Region, Transport Airplane Directorate, 17900 Pacific Highway South, Seattle, Washington, or the Standardization Branch, 9010 East Marginal Way South, Seattle, Washington. This amendment (39-6632, AD 90-13-08) becomes effective on July 23, 1990.
2001-15-07: This amendment adopts a new airworthiness directive (AD), applicable to certain Aerospatiale Model ATR42-200, -300, and -320 series airplanes, that requires modifying the wiring of the starting rotary switch. The actions specified by this AD are intended to prevent the loss of electrical power supply of the direct current (DC) emergency and standby buses, which could result in the loss of some electrical loads and the consequent display of erroneous information to the flight crew. This action is intended to address the identified unsafe condition.
2025-13-04: The FAA is adopting a new airworthiness directive (AD) for all MHI RJ Aviation ULC Model CL-600-2C10 (Regional Jet Series 700, 701, & 702), CL-600-2C11 (Regional Jet Series 550), CL-600-2D15 (Regional Jet Series 705), CL-600-2D24 (Regional Jet Series 900), and CL-600-2E25 (Regional Jet Series 1000) airplanes. This AD was prompted by an engine indicating and crew alerting system (EICAS) STAB TRIM Caution message that was posted, and subsequent repair that found prematurely worn teeth on a rubber bull gear (RBG) wheel in the horizontal stabilizer trim actuator (HSTA). This AD requires an inspection for part numbers and on-condition replacement of affected RBG wheels. This AD also prohibits the installation of affected parts under certain conditions. The FAA is issuing this AD to address the unsafe condition on these products.
2001-14-21: This amendment adopts a new airworthiness directive (AD), applicable to certain Aerospatiale Model ATR42-200, -300, -320, and -500 series airplanes and Model ATR72 series airplanes, that requires temporarily revising the Airplane Flight Manual (AFM) to add tests of the engine fire protection system and conducting those tests prior to each flight. This amendment also requires replacement of defective engine fire handles with serviceable fire handles, which terminates the revision of the AFM and the repetitive tests of the engine fire protection system. These actions are necessary to prevent intermittent improper functioning of the engine fire handles, due to a machining defect of the control shaft bore guide, which could result in malfunction of the trigger (squib), and failure to activate one of the two engine fire extinguishers. This action is intended to address the identified unsafe condition.
55-01-01: 55-01-01 NAVION: Applies to All Models. Compliance required as indicated. Some Navion aircraft have been found to have cracks in fuselage frame 143-31004-16 at Station 294.1 inboard from the top stringer cutout at W.L. 21.00. It is therefore necessary that all Navions be inspected for this condition as soon as practicable but not later than March 15, 1955. Inspection may be made by removing the inspection plate on the left side of the fuselage beneath the horizontal stabilizer and looking forward to view the aft side of the points in question. If no crack is visible, no further immediate action is necessary, however, a thorough inspection of the frame at each 100-hour inspection will be required thereafter until the reinforcement indicated in item 2 or 3 as indicated below is completed. If a crack is visible at either side of the frame, determine if it has extended beyond the nearest rivet inboard of the cutout (hereafter called the critical rivet). If it hasnot, the repair as indicated in item 1 may be used as an interim fix in lieu of the permanent repair indicated in item 2 or 3 which is mandatory in the case of a crack extending beyond the critical rivet. 1. Interim repair for cracks not extending beyond the critical rivet: (a) When crack extends to the critical rivet, remove the rivet and relocate nearby or if crack has not reached the critical rivet, stopdrill end of crack. (b) Install a modified diamond-shaped 0.125 24ST alclad gusset to right and left outer fuselage surfaces catching two existing rivets on each side of frame through W.L. 21 stringer, five existing rivets through the frame above the stringer cutout and three existing rivets through frame below the cutout. Add two AD4 rivets through the frame between the three existing rivets below the cutout. Additional AD4 rivets through the gusset and skin should be added as necessary. (c) Check the cracked area at each 100-hour inspection to determine ifcrack has extended beyond the critical rivet. If so, it will be necessary to apply item 2 or 3. 2. Permanent Repair: (a) Remove the cracked frame and strip off the angles and doublers and attach to new frame. Do not notch new frame to receive top stringers. (b) Cut top stringers forward and aft of frame location. (c) Install new frame in fuselage and attach skin. Where rivets do not properly fill holes use next size larger rivet. (d) Secure top stringers forward of frame by adding a 0.040 24ST alclad angle 3 inches long to the forward portion of the stringer and attaching it to the frame flange with an existing AD4 rivet through the frame flange, skin and external gusset patch. (e) Install gusset patch as indicated in item 1(b). 3. In lieu of item 2, an equivalent frame repair in accordance with CAM 18 will be accepted as an alternate for a new frame. This, however, may be difficult due to the presence of existing doublers and stiffeners on the forward face of the frame which is further complicated by the attachment of the W.L. 21 shear web to the aft side of the frame. Such alternate repairs must be submitted to a FAA Aircraft Engineering office for approval prior to installation. (Ryan Field Service Bulletin No. 22 covers this same subject.)
86-21-03: 86-21-03 BRITISH AEROSPACE: Amendment 39-5421. Applies to BAe Model 125- 800A series airplanes, serial numbers listed in BAe Service Bulletin 24-250-(3017D), dated April 8, 1985, certificated in any category. Compliance is required within 90 days after the effective date of this AD. To prevent a potential fire hazard associated with chafing of electrical wiring, accomplish the following, unless previously accomplished: A. Inspect and replace, as necessary, the affected electrical cables and install the protective treatment to adjacent structures in accordance with BAe Service Bulletin 24-250- (3017D), dated April 8, 1985. B. 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. 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 inspections and/or modifications required by the AD. All persons affected by this directive who have not already received the appropriate service bulletin from the manufacturer may obtain copies upon request to British Aerospace, Inc., Librarian, Box 17414, Dulles International Airport, Washington, D.C. 20041. This document may be examined at 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 October 24, 1986.
2016-23-06: We are adopting a new airworthiness directive (AD) for various aircraft equipped with a BRP-Powertrain GmbH & Co KG (formerly Rotax Aircraft Engines) 912 A series engine. 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 manufacturing defect found in certain carburetor floats where an in-flight engine shutdown and forced landing could occur when the affected cylinder had reduced or blocked fuel supply. We are issuing this AD to require actions to address the unsafe condition on these products.
2010-23-14: 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: Several cases of corrosion in lower structural members of the passenger door have been reported. It was subsequently determined that a drainage ramp (constructed from resin) had deteriorated with time and was retaining moisture. * * * Corrosion left undetected could eventually affect the structural integrity of the door and surrounding structure. We are issuing this AD to require actions to correct the unsafe condition on these products.
79-10-02: 79-10-02 SHORT BROTHERS LIMITED: Amendment 39-3457. Applies to Model SD3-30 airplanes, S/N SH3002 through SH3019, certificated in all categories, which have low blade angle pitch mechanism support bracket, P/N SD3-49-0784, or P/N SD3-49-0784xB installed. Compliance is required as indicated, unless already accomplished. To prevent propeller blade angle from increasing beyond the flight setting, accomplish the following: (a) Within the next 30 hours time in service after the effective date of this AD, remove each low blade angle pitch mechanism support bracket, P/N SD3-49-0784 or P/N SD3- 49-0784xB, and inspect it for cracks using the dye penetrant procedure or an equivalent FAA- approved procedure, in accordance with paragraph 2.A., "Accomplishment Instructions", of Short Brothers Service Bulletin No. SD3-61-A05, dated August 2, 1978, or an FAA-approved equivalent. (b) Within the next 300 hours time in service after bracket reinstallation in accordance with paragraph (c)(1) of this AD or bracket replacement in accordance with paragraph (d)(1) of this AD, and thereafter at intervals not to exceed 300 hours from the last inspection, visually inspect support bracket, P/N SD3-49-0784 or P/N SD3-49-0784xB, for cracks in accordance with paragraph 2.A.10 of the Short Brothers Service Bulletin No. SD3-61- A05 dated August 2, 1978, or an FAA-approved equivalent. (c) If, during any inspection required by paragraph (a) of this AD, no cracks are found (1) Reinstall support bracket, P/N SD3-49-0784 or P/N SD3-49-0784xB in accordance with Short Brothers Service Bulletin No. SD3-61-A05 dated August 2, 1978, or an FAA-approved equivalent and accomplish the repetitive inspections required by paragraph (b) of this AD; or (2) Install a modified support bracket, P/N SD3-49-0902 or P/N SD3-49- 0902xA in accordance with Short Brothers Service Bulletin No. SD3-61-05 dated September 27, 1978, or an equivalent approved by the Chief, Aircraft Certification Staff, FAA, Europe, Africa and Middle East Region. (d) If, during any inspection required by this AD, any cracks are found, remove the cracked bracket from service and - (1) Replace the cracked support bracket with a crack-free, new or used support bracket of the same part number, and accomplish the repetitive inspections required by paragraph (b) of this AD. (Before installation of a used support bracket, inspect it in accordance with the method specified in paragraph (a) of this AD to ensure that it is crack-free); or (2) Replace the cracked bracket with a modified support bracket, P/N SD3- 49-0902 or P/N SD3-49-0902xA, in accordance with Short Brothers Service Bulletin No. SD3- 61-05 dated September 27, 1978, or an equivalent approved by the Chief, Aircraft Certification Staff, FAA, Europe, Africa and Middle East Region. (e) Upon installation of a modified support bracket, P/N SD3-49-0902 or P/N SD3- 49-0902xA, in accordance with Short Brothers Service Bulletin No. SD3-61-05 dated September 27, 1978, or an equivalent approved by the Chief, Aircraft Certification Staff, FAA, Europe, Africa, and Middle East Region, inspections required by paragraph (b) of this AD may be discontinued. (f) Upon request of an operator, the Chief, Aircraft Certification Staff, FAA, Europe, Africa and Middle East Region, c/o American Embassy, Brussels, Belgium, may adjust the repetitive inspection interval specified in paragraph (b) of this AD or approve modifications equivalent to that specified in paragraphs (c), (d), and (e) of this AD provided that such requests are made through an FAA maintenance inspector and the request contains substantiating data to justify the request for that operator. This amendment becomes effective May 14, 1979.
94-21-03: This amendment adopts a new airworthiness directive (AD), applicable to certain Jetstream Model 4101 airplanes, that requires installation of a placard near the decouple control handle for the elevator control system to ensure that the pilots are made aware that maintenance action is required to reset the disconnect unit once the decouple control handle has been pulled. This amendment is prompted by a report that, if the decouple control handle for the elevator control system is pulled, the lock linkage will remain unlocked until it is reset during maintenance. The actions specified by this AD are intended to prevent reduced controllability of the airplane due to loss of the mechanical linkage between the pilots' elevator controls, and each pilot having control authority over only one-half of the elevator control system.
2016-21-06: We are superseding Airworthiness Directive (AD) 2015-02-23, for certain Bombardier, Inc. Model CL-600-1A11 (CL-600), CL-600-2A12 (CL-601), and CL-600-2B16 (CL-601-3A and CL-601-3R Variants) airplanes. AD 2015-02-23 required repetitive inspections for fractured or incorrectly oriented fasteners on the inboard flap hinge-box forward fittings on both wings, and replacement of all fasteners if necessary. This new AD also requires replacement of the fasteners, which terminates the requirements of this AD. This AD was prompted by reports of incorrectly oriented fasteners. We are issuing this AD to prevent incorrectly oriented or fractured fasteners, which could result in detachment of the flap hinge-box and the flap surface, and consequent reduced controllability of the airplane.
2001-15-05: This amendment adopts a new airworthiness directive (AD), applicable to all Aerospatiale Model ATR42-200, -300, -320, -500, and ATR72 series airplanes, that requires a revision of the Airplane Flight Manual to add instructions that prohibit the flightcrew from selecting the reverse position on the engines in the event of propeller thrust dissymmetry. The actions specified by this AD are intended to ensure that the flightcrew is advised of the hazard associated with selecting reverse thrust during propeller thrust dissymmetry, which could result in reduced controllability of the airplane during landing. This action is intended to address the identified unsafe condition.
2022-26-01: The FAA is adopting a new airworthiness directive (AD) for certain GE Aviation Czech s.r.o. (GEAC) M601D-11, M601E-11, M601E-11A, M601E-11AS, M601E-11S, M601F, H75-100, H75-200, H80, H80-100, H80-200, H85-100, and H85-200 model turboprop engines. This AD was prompted by reports of cracks in dilution tube weld areas of the combustion chamber outer liner. This AD requires initial and repetitive borescope inspections (BSIs) of the dilution tube weld areas of the combustion chamber outer liner and, depending on the results of the inspections, replacement of the combustion chamber outer liner with a part eligible for installation. The FAA is issuing this AD to address the unsafe condition on these products.