Results
78-12-10: 78-12-10 SHORT BROTHERS LIMITED: Amendment 39-3236. Applies to Model SD3-30 airplanes certificated in all categories. Compliance is required prior to the accumulation of 4000 landings or prior to accumulating 25 landings after the effective date of this AD, whichever occurs later, unless already accomplished, and thereafter at intervals not to exceed 4000 landings. To prevent failure of the rod end bearing of the nose wheel steering actuator, replace the rod end bearing, P/N MS 21242S8K, with a new part of the same part number in accordance with Section 10, "Accomplishment Instructions" of Menasco Manufacturing Service Bulletin 32-21, dated January 11, 1978, or an FAA approved equivalent. NOTE: Short Brothers Limited Service Bulletin SD3-32-37 covers this same subject. This amendment becomes effective June 26, 1978.
96-18-04: This amendment supersedes two existing airworthiness directives (AD), applicable to certain Boeing Model 737-300, -400, and -500 series airplanes, that currently require modification of the packing and slide containers of the escape slide, and repetitive inspections of the velcro girt retaining straps of the escape slides at the forward door. The existing AD's were prompted by reports of slide girt material interfering with the girt bar stowage brackets during door opening. This new amendment requires the installation of a new modification, which constitutes terminating action for the repetitive inspection requirements. The actions specified by this amendment are intended to prevent failure or interference of opening of the forward doors, which could delay or impede the evacuation of passengers during an emergency.
2021-04-21: The FAA is adopting a new airworthiness directive (AD) for certain Airbus Helicopters Model EC120B helicopters. This AD was prompted by a report of broken and bent attachment bolts of the main rotor (MR) hub scissors assembly. This AD requires an inspection of the attachment bolts of the MR hub scissors assembly for discrepancies and repair if necessary; part marking of the attachment bolts of the MR hub scissors assembly; and repetitive inspections of the part marking of the attachment bolts, and repair if necessary; 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.
2021-05-15: The FAA is adopting a new airworthiness directive (AD) for certain Airbus Helicopters Model AS332C, AS332C1, AS332L, and AS332L1 helicopters. This AD was prompted by a report that the cabin lateral sliding plug door failed its emergency jettisoning test; subsequent investigation revealed that the jettison handle cable interfered with the cable clamps. This AD requires modifying the release system of each cabin lateral sliding plug door, or modifying the design of the jettison system of each cabin lateral sliding plug door, 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.
91-21-12: 91-21-12 BOEING: Amendment 39-8059. Docket No. 91-NM-86-AD. \n\n\tApplicability: Model 737, 757, and 747-400 series airplanes, equipped with Boeing part number (P/N) 285U0037-104, -105, -201, -202, or -203 series radio control panels, certificated in any category. \n\n\tCompliance: Required within 12 months of the effective date of this AD unless previously accomplished. \n\n\tTo prevent uncommanded frequency changes of the high frequency (HF) and very high frequency (VHF) radios, accomplish the following: \n\n\t(a)\tRemove the P/N 285U0037-104, -105, -201, -202, or -203 series radio control panels and replace them with panels approved by the Manager, Seattle Aircraft Certification Office (ACO), FAA, Transport Airplane Directorate. \n\n\t(b)\tAn 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, Seattle Aircraft Certification Office (ACO), 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, Seattle ACO. \n\n\t(c)\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\tThis amendment (39-8059, AD 91-21-12) becomes effective on November 12, 1991.
96-16-07: This amendment adopts a new airworthiness directive (AD) that is applicable to General Electric Company (GE) CF6-80C2 series turbofan engines. This action supersedes priority letter AD 96-09-01 that currently requires borescope inspections of the rear right hand mount link to determine if the serial number matches those listed in applicable service bulletins as improperly manufactured, and replacement, if necessary, with a serviceable part. This action references a newly revised service bulletin and bases the compliance time on the effective date of this superseding AD for engines installed on McDonnell Douglas MD-11 series aircraft. This amendment is prompted by the availability of the newly revised service bulletin. The actions specified by this AD are intended to prevent rear right hand mount link failure, which could result in engine separation from the aircraft.
96-08-01 R1: This amendment revises airworthiness directive (AD) 96-08-01, that is applicable to Hamilton Standard Model 14RF-9 propellers. The current AD superseded priority letter AD 95-24- 09, and requires an ultrasonic shear wave inspection, adds a one-time visual and fluorescent penetrant inspection, and repair of the propeller blade shank. This revision will add a new shank eddy current inspection and will allow repair of certain blade shanks removed from service under the current AD. The actions specified by this AD are intended to prevent propeller blade separation due to propeller blade shank cracking that can result in loss of control of the aircraft.
74-24-13: 74-24-13 UNITED INSTRUMENTS, INC.: Amendment 39-2028. Applies to P/N 5932 ( ) (Serial Numbers 47851 thru 69000) and P/N 5934 ( ) (Serial Numbers 70,000 thru 102,000, A1 thru A9999, B1 thru B9999, and C1 thru C2860) altimeters installed on various aircraft, such as Piper, Beech, Cessna, Bell, Aero Commander, Schweizer, Enstrom, Helio, American Aviation, Bellanca, et al. Note 1: United Instruments P/N 5932 ( ) altimeters may be additionally identified as TKK Model LA 4 TSO C-10b. United Instrument P/N 5934 ( ) altimeters may be additionally identified as TKK Model LA 7 TSO C-10b. Note 2: These altimeters may also be identified by various aircraft manufacturer's part numbers. Some but not all are: Beech: P/N 50-380094-( ), 50-384119-( ), 58-380011-( ), 58-380012-( ), 58-380041-( ), 100-324056-( ), 169-380073-( ) Cessna: P/N C661011-( ), C661071-( ), C661025-( ), C661014-( ) Piper: P/N 99009-( ), 450-611-( ), 450-694-( ), PS50008-( )-( ), 550-488-( ), 550-489-( ), 550-490-( ), 550-491-( ), 550-492-( ), 550-493-( ), 322-81-03, 322-81-04 Bell: P/N 206-070-263-( ), 47-711-303-( ) Compliance: Required as indicated, unless already accomplished. To prevent being deprived of altimeter readings during certain aircraft operating conditions, accomplish the following: A) Within the next 10 hours' time in service after the effective date of this AD, check each altimeter installed in all aircraft or check the aircraft's permanent maintenance record to determine if the altimeter falls within the Part Number and Serial Number designations set forth in the applicability statement. The owner/operator of the aircraft may make these checks. B) If, as a result of the determinations required by Paragraph A, an altimeter falls within the Part Number and Serial Number designations in the applicability statement, prior to further flight, either comply with Paragraph C or install a placard on the instrument panel in clear view of the pilot which states: "AIRCRAFT APPROVED FOR DAY VFR FLIGHT ONLY" and operate the aircraft in accordance with this limitation. C) On or before November 30, 1976, on any altimeter which falls within the Part Number and Serial Number designations set forth in the applicability statement, either replace the altimeter with an approved replacement part, an altimeter from outside the applicable Serial Numbers, or modify the existing altimeter in accordance with the United Instruments, Inc., Service Bulletin No. 1, dated September 19, 1974, or subsequent approved revisions. A modified altimeter will be identified by a 1/4-inch white dot painted alongside the nameplate on the back of the case. Upon compliance with this paragraph, the requirements of Paragraph B are no longer applicable. D) Any alternate means of compliance with this AD must be approved by the Chief, Engineering and Manufacturing Branch, FAA, Central Region. E) Compliance with Paragraph B of this AD is notrequired if the aircraft has two sensitive altimeters installed. In the event of failure of one of the altimeters, where both altimeters are noted in the applicability statement, compliance with Paragraph B and/or C is required. This amendment becomes effective December 5, 1974.
2021-07-15: The FAA is superseding Airworthiness Directive (AD) 82-20-05 for Societe Nationale Industrielle Aerospatiale (now Airbus Helicopters) Model AS-350 and AS-355 series helicopters. AD 82-20-05 required inspecting and establishing a life limit for the tail rotor (TR) drive shaft bearing (bearing). This new AD requires replacing certain part-numbered TR bearings with one part-numbered bearing and repetitively inspecting one part-numbered bearing. This AD was prompted by inconsistencies that have been identified between inspections and maintenance actions required by ADs and inspections and maintenance actions specified in the applicable maintenance manual. The actions of this AD are intended to address an unsafe condition on these products.
96-12-25: This document publishes in the Federal Register an amendment adopting Airworthiness Directive (AD) AD 96-12-25 which was sent previously to all known U.S. owners and operators of Bell Helicopter Textron, Inc. (BHTI) Model 204B helicopters by individual letters. This AD requires a visual inspection of each tail rotor (T/R) blade (blade) for peeling, flaking, or bubbling paint that may indicate corrosion; an inspection for corrosion, if necessary; and replacement of the T/R blade with an airworthy blade if corrosion is discovered. This amendment is prompted by an FAA determination, based on the manufacturer's data, that certain serial-numbered T/R blades were manufactured with internal leading edge doublers fabricated from clad aluminum instead of bare aluminum material. The actions specified by this AD are intended to prevent debonding of the main spar internal leading edge doubler, which could lead to failure of a T/R blade and subsequent loss of control of the helicopter.
2021-07-08: The FAA is superseding Airworthiness Directive (AD) 97-26-02 for Eurocopter Deutschland GmbH Model BO-105A, BO-105C, BO-105S, BO- 105LS A-1, and BO-105LS A-3 helicopters; and Eurocopter Canada Ltd. Model BO-105LS A-3 helicopters. AD 97-26-02 required a repetitive visual inspection for cracks in the ribbed area of the main rotor (M/R) mast flange (flange), and depending on the outcome, replacing the M/R mast. This new AD retains the requirements of AD 97-26-02 and removes the reinforced M/R mast from the applicability. This AD was prompted by the determination that a certain reinforced M/R mast is not affected by the unsafe condition. The actions of this AD are intended to address an unsafe condition on these products.
96-14-05: This amendment supersedes an existing airworthiness directive (AD), applicable to certain Boeing Model 767 series airplanes, that currently requires an inspection of the control rods of the outboard leading edge slat, and follow-on actions (including repetitive ultrasonic inspections), if necessary. For certain airplanes, that AD also requires replacement of the control rod ends and attach bolts. It also provides for an optional terminating action for follow-on repetitive inspections. That AD was prompted by reports of cracks and worn attach bolts of the control rods of the leading edge outboards slats of the wings due to the high breakout torque in the joint of the control rod end. This amendment requires the installation of the previously optional terminating action. The actions specified by this AD are intended to prevent reduced controllability of the airplane and damage in the slat structure or fixed leading edge of the wing, as a result of cracks and worn attach bolts.
2021-06-02: The FAA is adopting a new airworthiness directive (AD) for all Airbus Helicopters Model AS332L, AS332L1, AS332C, and AS332C1 helicopters. This AD was prompted by the failure of a second stage planet gear installed in the main gearbox (MGB). This AD requires identifying the part number of each second stage planet gear assembly installed in the MGB, replacing an MGB having certain second stage planet gear assembly part numbers with a serviceable MGB, modifying the helicopter by installing a full flow magnetic plug (FFMP), repetitively inspecting the FFMP and the MGB bottom housing and conical housing for metal particles, analyzing any metal particles that are found, and applying corrective actions if necessary, as specified in European Union Aviation Safety Agency (EASA) ADs, which are incorporated by reference. The FAA is issuing this AD to address the unsafe condition on these products.
92-13-08: 92-13-08 BOEING: Amendment 39-8278. Docket No. 92-NM-13-AD.\n\n\tApplicability: Model 747-400 series airplanes; as listed in Boeing Alert Service Bulletin 747-38A2090, dated November 21, 1991; certificated in any category.\n\n\tCompliance: Required within 12 months after the effective date of this AD, unless accomplished previously.\n\n\tTo prevent fires in the drain mast internal space, accomplish the following:\n\n\t(a)\tInstall shields with sealant over the mid and aft drain masts in accordance with Boeing Alert Service Bulletin 747-38A2090, dated November 21, 1991.\n\n\t(b)\tInstall moisture resistant and thermal insulation tape around the forward drain tube and heater elements on the mid and aft drain masts in accordance with Boeing Alert Service Bulletin 747-38A2090, dated November 21, 1991.\n\n\t(c)\tAn 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, Seattle Aircraft Certification Office (ACO), FAA, Transport Airplane Directorate. Operators shall submit their requests through an FAA Principal Maintenance Inspector, who may concur or comment and then send it to the Manager, Seattle ACO.\n\n\tNOTE: Information concerning the existence of approved alternative methods of compliance with this airworthiness directive, if any, may be obtained from the Manager, Seattle ACO.\n\n\t(d)\tSpecial 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.\n\n\t(e)\tThe installations shall be done in accordance with Boeing Alert Service Bulletin 747-38A2090, dated November 21, 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 Boeing Commercial Airplane Group, P. O. Box 3707, Seattle, Washington 98124. Copies may be inspected at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, Washington; or at the Office of the Federal Register, 1100 L Street NW., Room 8401, Washington, DC.\n\n\t(f)\tThis amendment becomes effective on August 5, 1992.
2021-05-18: The FAA is superseding Airworthiness Directive (AD) 2019-06-06 for all International Aero Engines AG (IAE) V2500-A1, V2522-A5, V2524- A5, V2525-D5, V2527-A5, V2527E-A5, V2527M-A5, V2528-D5, V2530-A5, and V2533-A5 model turbofan engines. AD 2019-06-06 required initial and repetitive borescope inspections (BSIs) of the M-flange and, if it fails the inspection, replacement of the diffuser case with a part eligible for installation. This AD requires an initial BSI of the M- flange and, if it fails the inspection, repetitive BSIs of the M-flange until replacement of the diffuser case M-flange. The FAA is issuing this AD to address the unsafe condition on these products.
96-13-01: This amendment adopts a new airworthiness directive (AD) that applies to MDB Flugtechnik AG Model MD3-160 airplanes. This action requires inserting a supplement Aircraft Flight Manual (AFM), installing a placard prohibiting aerobatics and spinning, inspecting the nosewheel steering system for damaged parts and improper rigging, and if necessary, replacing the parts and re-rigging the nosewheel steering system (NWS). Two incidents on certain MD3-160 airplanes while in flight causing the airplanes to go into a left spin and loose rudder control prior to landing prompted this AD action. The actions specified by this AD are intended to prevent the rudder pedals from locking up and the nosewheel steering from disengaging, which if not detected and corrected, could cause loss of control of the airplane.
2021-05-17: The FAA is superseding Airworthiness Directive (AD) AD 2019- 12-09 for certain Rockwell Collins, Inc. (Rockwell Collins) FDSA-6500 flight display system applications installed on airplanes. AD 2019-12- 09 imposed operating limitations on the traffic collision avoidance system (TCAS). AD 2019-12-09 was prompted by conflict between the TCAS display indications and aural alerts that may occur during a resolution advisory (RA) scenario. This AD retains the requirements of AD 2019-12- 09 until a software upgrade is completed. The FAA is issuing this AD to address the unsafe condition on these products.
78-12-02: 78-12-02 SCOTTISH AVIATION LIMITED: Amendment 39-3230. Applies to "Beagle" Model B206 Series II airplanes, certificated in all categories, which have exhaust system bellows assembly, P/N CE20901 or P/N CE 20806, installed. Compliance required as indicated, unless already accomplished. To minimize the possibility of hot exhaust gases escaping from a fractured exhaust bellows assembly and impinging on the tachometer electrical leads and other engine compartment components, accomplish the following: (a) Within the next 25 hours time in service after the effective date of this AD, inspect the exhaust system bellows assemblies, Part Number CE 20901 and Part Number CE 20806, for cracks, corrosion, and deterioration in accordance with paragraph 3(a) of Scottish Aviation Limited Service Bulletin No. B206/55 Issue 2, dated January 5, 1976, or an FAA approved equivalent, (hereinafter referred to as the Service Bulletin). (b) If a crack, corrosion, or deterioration is not found during the inspection required by paragraph (a) of this AD - (1) Within 50 hours time in service after the inspection required by paragraph (a) of this AD and, thereafter, at intervals not to exceed 50 hours time in service, inspect the bellows assemblies in accordance with paragraph 3(b) of the Service Bulletin; and (2) Within 100 hours time in service, or 3 months after the inspection required by paragraph (a), whichever occurs sooner, and, thereafter, at intervals not to exceed 100 hours time in service or 3 months, whichever occurs sooner, inspect the bellows assemblies in accordance with paragraph 3(a) of the Service Bulletin. (c) If a crack, corrosion, or deterioration is found during any inspection required by this AD, replace the affected bellows assembly with a serviceable part of the same part number. (d) For bellows assemblies installed as replacements - (1) Within 50 hours time in service after installation and, thereafter, at intervals not to exceed 50 hours time in service, inspect the bellows assemblies in accordance with paragraph 3(b) of the Service Bulletin; (2) Within 200 hours time in service, or 6 months, after installation, whichever occurs sooner, and, thereafter, at intervals not to exceed 100 hours time in service or 3 months, whichever occurs sooner, inspect the bellows assemblies in accordance with paragraph 3(a) of the Service Bulletin. This amendment becomes effective June 22, 1978.
2021-07-05: The FAA is superseding Airworthiness Directive (AD) 2007-26-52 which applied to certain Agusta S.p.A. (now Leonardo) Model A109C, A109E, and A109K2 helicopters. AD 2007-26-52 required inspecting for swelling, deformation, bonding separation, and for a crack on each main rotor blade (MRB) with a certain part-numbered tip cap installed, and removing the MRB from service before further flight if any of these conditions exist and exceed the prescribed limits. This AD retains all inspections for certain serial-numbered MRBs, but for MRBs with a certain tip cap installed, this AD requires dye-penetrant inspections rather than visual inspections. This AD was prompted by additional reports of in-flight loss of part of a tip cap. The FAA is issuing this AD to address the unsafe condition on these products.
96-12-20: This amendment supersedes an existing airworthiness directive (AD), applicable to certain Lockheed Model 382, 382B, 382E, 382F, and 382G series airplanes, that currently requires visual inspections to detect loose, missing, or deformed fasteners in the upper truss mounts of certain engines, inspections to detect cracking in the associated tangs, and replacement of damaged parts. This amendment adds a requirement for repetitive ultrasonic inspections to detect cracking of the upper tangs and replacement of cracked parts. This amendment also provides for an optional terminating action for the repetitive inspections, and revises the applicability of the rule to specify groupings of airplanes. This amendment is prompted by reports indicating that fatigue cracking of the tangs of the upper truss mount has been detected. The actions specified by this AD are intended to prevent multiple failures of the upper truss mounts due to problems associated with fatigue cracking, which could adversely affect the integrity of the engine mount structure. The incorporation by reference of Hercules Service Bulletin 382-71-20, dated March 18, 1994, as listed in the regulations, is approved by the Director of the Federal Register as of July 15, 1996. The incorporation by reference of Lockheed Alert Service Bulletin A382-71-19/A82-687, dated December 23, 1993, as listed in the regulations, was approved previously by the Director of the Federal Register as of February 18, 1994 (59 FR 5078, February 3, 1994).
2021-05-12: The FAA is adopting a new airworthiness directive (AD) for certain Airbus SAS Model A330-200 Freighter series airplanes. This AD was prompted by a determination that new or more restrictive airworthiness limitations are necessary. This AD requires revising the existing maintenance or inspection program, as applicable, to incorporate new or more restrictive airworthiness limitations, as specified in a European Union Aviation Safety Agency (EASA) AD, which is incorporated by reference. The FAA is issuing this AD to address the unsafe condition on these products.
96-02-03: This amendment supersedes an existing airworthiness directive (AD), applicable to all Airbus Model A310 series airplanes, that currently requires inspections to detect cracks in the area of the shock absorber attachment at the top of the barrel at the main landing gear (MLG), a measurement of the gap between the barrel and the shock absorber attachment; and corrective action, if necessary. That AD was prompted by a report of the rupture of the aft hinge arm of the left MLG barrel. This amendment requires a measurement of the gap between the washer and barrel of the MLG, eddy current inspections to detect cracking of the MLG barrel, correction of any discrepancy, and accomplishment of certain other follow-on actions. Terminating actions are also provided by this AD. The actions specified by this AD are intended to prevent collapse of the MLG.
91-23-01: 91-23-01 BEECH: Amendment 39-8070. Docket No. 91-CE-10-AD. Applicability: Model 77 (Skipper) airplanes (serial numbers WA-1 through WA-312) that do not have a part number (P/N) 108-820010-653 nose landing gear fork and axle assembly installed, certificated in any category. Compliance: Required as indicated, unless already accomplished. To prevent failure of the nose landing gear fork and the airplane damage that could result, accomplish the following: (a) Within the next 50 hours time-in-service (TIS) after the effective date of this AD, fluorescent penetrant inspect the nose landing gear fork for cracks in accordance with the instructions in Beech Service Bulletin (SB) No. 2241, Revision 1, dated January 1991. (1) If any crack is found, prior to further flight, remove and replace the nose landing gear fork and axle assembly with a (P/N) 108-820010-653 fork and axle assembly, and the requirements of this AD have been accomplished. (2) If no cracks are found, accomplish the following: (i) Fluorescent penetrant inspect the nose landing gear fork axle assembly at intervals not to exceed 500 hours TIS after the initial inspection required in paragraph (a) of this AD in accordance with the instructions in Beech SB No. 2241, Revision 1, dated January 1991; and visually inspect the nose landing gear fork axle assembly at every 100- hour TIS interval between the fluorescent penetrant inspections. (ii) If any crack is found as a result of any of the inspections in paragraph (a)(2)(i) of this AD, prior to further flight, remove and replace the nose landing gear fork and axle assembly with a (P/N) 108-820010-653 fork and axle assembly, and the repetitive inspections are no longer required. (b) Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate airplanes to a location where the requirements of this AD can be accomplished. (c) An alternative method of compliance or adjustmentof the initial or repetitive compliance times that provides an equivalent level of safety may be approved by the Manager, Wichita Aircraft Certification Office, FAA, 1801 Airport Road, Mid-Continent Airport, Wichita, Kansas 67209. The request should be forwarded through an appropriate FAA Maintenance Inspector, who may add comments and then send it to the Manager, Wichita Aircraft Certification Office. (d) The inspections required by this AD shall be done in accordance with Beech Service Bulletin No. 2241, Revision 1, dated January 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 the Beech Aircraft Corporation, P.O. Box 85, Wichita, Kansas 67201-0085. Copies may be inspected at the FAA, Central Region, Office of the Assistant Chief Counsel, Room 1558, 601 E. 12th Street, Kansas City, Missouri, or at the Office of the Federal Register, 1100 L Street, NW, Room 8401, Washington, DC. This amendment (39-8070, AD 91-23-01) becomes effective on December 3, 1991.
96-11-06: This amendment adopts a new airworthiness directive (AD), applicable to certain de Havilland Model DHC-7 series airplanes, that requires modification of the emergency lights circuitry. This amendment is prompted by reports of the emergency lights turning on inadvertently due to voltage spikes from other equipment; and reports that the existing emergency light switch arrangement allows the flight compartment and flight attendant's panel switches to override each other. The actions specified by this AD are intended to prevent such failures of the emergency light systems, which could prevent the use of the emergency lights in the event of an emergency.
96-10-14: This amendment supersedes Airworthiness Directive (AD) 88-05-05, which currently requires the following on certain The New Piper Aircraft, Inc. (Piper) PA31, PA31P, and PA31T series airplanes: repetitively inspecting both the left and right main landing gear (MLG) forward sidebrace, and replacing any cracked MLG forward sidebrace. The Federal Aviation Administration's policy on aging commuter-class aircraft is to eliminate or, in certain instances, reduce the number of certain repetitive short-interval inspections when improved parts or modifications are available. This action retains the current repetitive inspection and necessary replacement requirements contained in AD 88-05-05, and requires incorporating both a left and right MLG forward sidebrace of improved design as terminating action for the repetitive inspection requirement. The actions specified in this AD are intended to prevent the MLG from retracting because of a cracked MLG forward sidebrace, which, if not detected and corrected, could result in gear collapse and loss of control of the airplane during landing operations.