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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.
90-26-54: 90-26-54 BOEING: Amendment 39-6994. Docket 90-NM-284-AD. Final Rule of telegraphic AD. \n\n\tApplicability: All Model 747-400 series airplanes, certificated in any category. \n\n\tCompliance: Required within 10 days after the effective date of this AD, unless previously accomplished. \n\n\tTo prevent uncommanded leading edge flap retraction during takeoff roll, accomplish the following: \n\n\tA.\tRevise the Limitations Section of the FAA-approved Airplane Flight Manual (AFM) to add the following statement. This may be accomplished by inserting a copy of this AD in the AFM. \n\n\t\t"Dispatch with an inoperative thrust reverser is prohibited." \n\n\tB.\tAn alternate means of compliance or adjustment of the compliance time, which provides an acceptable level of safety, may be used when approved by the Manager, Seattle Aircraft Certification Office (ACO), FAA, Transport Airplane Directorate. \n\n\tNOTE: The request should be submitted directly to the Manager, Seattle ACO, and a copy sent to the cognizant FAA Principal Inspector (PI). The PI will then forward comments or concurrence to the Seattle ACO. \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\tThis amendment (39-6994, AD 90-26-54) becomes effective on May 29, 1991, as to all persons, except those persons to whom it was made immediately effective by telegraphic AD T90-26-54, issued December 24, 1990, which contained this amendment.
2021-05-13: The FAA is adopting a new airworthiness directive (AD) for Leonardo S.p.a. (Leonardo) Model AW189 helicopters. This AD was prompted by two reported failures of the tail plane installation forward bolts (bolts). This AD requires inspecting the bolts and depending on the results of those inspections, removing certain parts from service or installing a tail plane retromod. This AD also requires torqueing certain part-numbered nuts, inspecting bolts and nuts for wear, and depending on the results of those inspections, removing parts from service. The FAA is issuing this AD to address the unsafe condition on these products.
2021-06-06: The FAA is superseding Emergency Airworthiness Directive (AD) 2021-05-52 which applied to certain Bell Textron Canada Limited (Bell) Model 505 helicopters. Emergency AD 2021-05-52 required a one-time visual inspection of the pilot collective stick and grip assembly (pilot collective stick), a fluorescent penetrant inspection (FPI) if no crack was found during the visual inspection, and depending on the inspection results, removing the pilot collective stick from service and reporting certain information to Bell. Emergency AD 2021-05-52 also prohibited installing any pilot collective stick on any helicopter unless the inspections had been accomplished. This AD removes the visual inspection of the pilot collective stick, requires repetitive FPIs of the pilot collective stick, and requires revising the existing Rotorcraft Flight Manual (RFM) for your helicopter. This AD retains the reporting requirement and expands the prohibition. This AD was prompted by the determination that visual inspections do not adequately detect a crack and additional findings that a crack may occur sooner than previously expected. The FAA is issuing this AD to address the unsafe condition on these products.
97-04-05: This amendment adopts a new airworthiness directive (AD) that is applicable to certain Jetstream Model 4101 airplanes. This action requires a one-time inspection of the airplane records to determine the modification status of the elevator trim servo, and, if necessary, inspections to determine the serial number of the servo, and repetitive inspections for looseness or movement of the motor housing of the servo. This action also requires replacement of certain elevator trim servos with a serviceable assembly. This amendment is prompted by reports of the motor housing separating from the elevator trim servo and the consequent release of certain component parts, due to inadequate locking of screws that were installed during assembly of the servos. The actions specified in this AD are intended to prevent the motor housing of the elevator trim servo from separating and releasing component parts that could lodge in and jam the elevator controls, and result in reduced pitch control of the airplane.
96-10-06: This amendment adopts a new airworthiness directive (AD) that is applicable to certain Boeing Model 737 series airplanes. This action requires repetitive inspections to detect cracks of the lower gate hinge of the forward galley service door, and replacement of any cracked hinge. This action also provides an optional terminating replacement for the repetitive inspections. This amendment is prompted by reports of fatigue cracks found in the lower gate hinge on the forward galley service door. The actions specified in this AD are intended to prevent such fatigue cracking, which could lead to the failure of the lower gate hinge on the forward galley service door and subsequent loss of cabin pressure. If the hinge fails, the hinge and its associated mechanisms and the emergency escape slide could separate from the airplane and be ingested into the engine, or could strike and damage the flight control surfaces.
96-10-13: This amendment supersedes Airworthiness Directive (AD) 84-08-06, which currently requires the following on certain The New Piper Aircraft, Inc. (Piper) Models PA31T, PA31T1, PA31T2, and PA31T3 airplanes: repetitively inspecting the fuselage station (FS) 332 bulkhead for cracks, and reinforcing or replacing the FS 332 bulkhead if cracks are found. 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 inspections contained in AD 84-08-06, and requires incorporating a stabilizer forward spar attachment bulkhead reinforcement kit or installing a reinforced bulkhead assembly as terminating action for the repetitive inspection requirement. The actions specified in this AD are intended to prevent structural failure of the horizontal stabilizer and the aftfuselage attachment caused by cracks in the FS 332 bulkhead, which, if not detected and corrected, could result in loss of control of the airplane.
2021-05-11: The FAA is superseding Airworthiness Directive (AD) 2017-26- 10, which applied to certain The Boeing Company Model 757 airplanes. AD 2017-26-10 required deactivating the spoiler control module (SCM) relays and capping and stowing the associated wiring on certain airplanes. This AD requires repetitive operational tests of the spoiler inhibit function. For certain airplanes, this AD requires installing a new relay bracket assembly, making changes to the wire bundles for certain SCMs, installing new SCMs, measuring the clearance between a wire bundle and the top of the new relay bracket assembly, and applicable on-condition actions. For a certain other airplane, this AD requires changing certain wire bundles. This AD was prompted by reports of unwanted lateral oscillations during landing operations, and the development of wiring changes for certain SCMs, which will improve the lateral handling qualities of the airplane during approach and landing. The FAA is issuing this AD to address the unsafe condition on these products.