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2013-05-02: We are adopting a new airworthiness directive (AD) for all The Boeing Company Model DC-9-81 (MD-81), DC-9-82 (MD-82), DC-9-83 (MD-83), DC-9-87 (MD-87), and MD-88 airplanes. This AD was prompted by reports of cracks of the hinge bearing lugs of the center section ribs of the horizontal stabilizer. This AD requires repetitive high frequency eddy current (HFEC) inspections for cracking of the left and right rib hinge bearing lugs of the aft face of the center section of the horizontal stabilizer; measuring crack length and blending out cracks; and replacing the horizontal stabilizer center section rib, if necessary. We are issuing this AD to detect and correct cracking in the hinge bearing lugs of the horizontal stabilizer center section ribs, which could result in failure of the lugs, and consequent inability of the horizontal stabilizer to sustain the required limit loads and loss of control of the airplane.
98-19-21: This amendment adopts a new airworthiness directive (AD) that is applicable to Rolls-Royce, plc RB211 Trent 800 series turbofan engines. This action requires initial and repetitive ultrasonic inspections of fan blade roots for cracks, and replacement, if necessary, with serviceable parts. This amendment is prompted by reports of multiple fan blade root cracks in several factory test engines. The actions specified in this AD are intended to prevent fan blade failure, which could result in multiple fan blade release, uncontained engine failure, and possible damage to the aircraft. The incorporation by reference of certain publications listed in the regulations is approved by the Director of the Federal Register as of October 7, 1998. Comments for inclusion in the Rules Docket must be received on or before November 23, 1998.
88-08-02: 88-08-02 DeHAVILLAND: Amendment 39-5889. Applies to all Model DHC-2 Mk. I (including L-20A, YL-20, U-6, and U-6A) and DHC-Mk. III (Turbo Beaver) (all serial numbers) airplanes with wing strut assemblies C2W1103, C2W1103A, C2W1104 and C2W1104A, certified in any category. COMPLIANCE: Required as indicated after the effective date of this AD, unless already accomplished. To detect cracks due to stress corrosion in wing lift strut assemblies, accomplish the following: (a) Within 100 hours time-in-service (TIS), or one month, whichever occurs first after the effective date of this AD, and thereafter at intervals not to exceed 500 hours TIS, or 12 calendar months, whichever occurs first: (1) Remove wing strut assemblies, C2W1103 or C2W1103A and C2W1104 or C2W1104A from the airplane and prepare the assemblies for inspection as described in the "ACCOMPLISHMENT INSTRUCTIONS" section of DeHavilland Service Bulletin (S/B) No. 2/41, Revision A, dated August 14, 1987.(2) Conduct a dye penetrant inspection with a 10-power glass for cracks in the lugs of the lower attachment clevis fitting. (3) If cracks are found, prior to further flight replace the complete strut assembly with a strut assembly of the same part number that has had the lower clevis fitting inspection using the dye penetrant procedure and has been found free of cracks, or strut assembly C2W1115-1 or C2W115-2, as appropriate. (4) If no cracks or found, clean the lower clevis fitting and reinstall the wing strut assembly. (5) If wing strut assembly C2W1115-1 or C2W1115-2 is installed, the recurring visual inspection specified in Paragraph (a) of this AD is no longer required. (b) The airplane may be flown in accordance with FAR 21.197 to a location where the requirements of this AD may be accomplished. (c) Upon submission of substantiating data by owner or operator through an FAA Maintenance Inspector, the Manager, New York Aircraft Certification Office,FAA, New England Region, may adjust the repetitive inspection intervals specified in this AD. (d) An equivalent means of compliance with this AD may be used if approved by the Manager, New York Aircraft Certification Office, FAA, New England Region. All persons affected by this directive may obtain copies of the document referred to herein upon request to the DeHavilland Aircraft Company of Canada, a Division of Boeing of Canada, Ltd., Garratt Boulevard, Downsview, Ontario, Canada, M3K 1Y5; telephone: (416) 633- 7310, or these documents may be examined at the FAA, Office of the Regional Counsel, Room 1558, 601 East 12th Street, Kansas City, Missouri 64106. This AD supersedes AD 87-01-04, Amendment 39-5488 (51 FR 45306; December 18, 1986). This amendment, 39-5889, becomes effective on May 11, 1988.
2022-09-05: The FAA is adopting a new airworthiness directive (AD) for certain Embraer S.A. Model ERJ 190-300, and -400 airplanes. This AD was prompted by a report of premature failures of the alternating current motor pump (ACMP) 3A at hydraulic system #3 due to excessive wear of the ACMP tail bearing. This AD requires repetitive replacement of the hydraulic system ACMP 3A having a certain part number with a serviceable part, as specified in an Ag[ecirc]ncia Nacional de Avia[ccedil][atilde]o Civil (ANAC) AD, which is incorporated by reference. The FAA is issuing this AD to address the unsafe condition on these products.
2013-04-13: We are adopting a new airworthiness directive (AD) for all BAE SYSTEMS (OPERATIONS) LIMITED Model BAe 146 and Avro 146-RJ series airplanes. This AD was prompted by a report that certain ceramic terminal blocks, through which the wiring for the engine fire extinguishers, fire detection circuits, and engine and intake anti-ice system are routed, have been found to have moisture ingress, which can degrade the insulation resistance of the ceramic terminal blocks. This AD requires a one-time insulation resistance test of ceramic terminal blocks, and if necessary, replacement of the blocks. We are issuing this AD to prevent latent failure of the number 2 fire bottle, which, in the event of an engine fire, could result in failure of the fire bottle to discharge when activated and possibly preventing the flightcrew from extinguishing an engine fire.
98-20-20: This amendment supersedes an existing airworthiness directive (AD), applicable to certain Boeing Model 747 series airplanes, that currently requires repetitive inspections for damage or cracking of the aft pressure bulkhead, and repair, if necessary. This amendment continues to require certain repetitive inspections for damage or cracking of the aft pressure bulkhead, and repair, if necessary. This amendment removes certain repetitive inspections for cracking of the bulkhead web to Y-ring lap joint area but retains the initial inspection for cracking in that area. This amendment also adds a one-time inspection from the forward side of the bulkhead to detect fatigue cracking of the upper segment of the bulkhead web, and follow-on corrective actions, if necessary. This amendment is prompted by reports indicating that the inspections required by the existing AD may not detect cracking of the bulkhead web in a timely manner. The actions specified in this AD are intended todetect and correct fatigue cracking of the upper segment of the bulkhead web, which could result in rapid depressurization of the airplane, and consequent reduced controllability of the airplane.
98-20-15: This amendment adopts a new airworthiness directive (AD), applicable to certain Saab Model SAAB 340B series airplanes, that requires a one-time inspection for moisture or other contamination of a certain wiring harness, electrical relay, and relay socket; a one-time inspection for electrical damage of the same electrical relay and socket; corrective actions, if necessary; and replacement of certain nut plates with new, improved parts. This amendment is prompted by issuance of mandatory continuing airworthiness information by a foreign civil airworthiness authority. The actions specified by this AD are intended to prevent a short circuit caused by fluid leakage, which could result in inability to retract the landing gear or require the use of emergency extension.
69-22-03: 69-22-03 AVIONS MARCEL DASSAULT: Amdt. 39-866. Applies to all Fan Jet Falcon and Fan Jet Falcon Series D Airplanes having Serial Numbers 73 and subsequent on which the production microswitch has been replaced with a switch that has not been modified. Compliance is required as indicated, unless already accomplished. To prevent the ingress of moisture in the landing gear microswitch assembly, within the next 50 hours' time in service after the effective date of this AD, replace the unmodified microswitch with a modified switch in accordance with Avions Marcel Dassault Service Bulletin No. 333, Revision 2, dated March 28, 1969, or later SGAC-approved issue, or an FAA-approved equivalent as follows: (a) NOSE LANDING GEAR, TELESCOPIC BAR Replace the switch P/N A1.23802 with modified switch P/N A1.23802 V1 V2. (b) NOSE LANDING GEAR, DOOR ACTUATING CYLINDER Replace the switch P/N A1.23801 with modified switch P/N A1.23801 V1 V2. (c) MAIN LANDING GEAR,DRAG STRUT ACTUATOR CYLINDER Replace the switch P/N A2.23802 with modified switch P/N A2.23802 V1 V2. (d) MAIN LANDING GEAR, DOOR ACTUATING CYLINDER Replace the switch P/N A2.23801 with modified switch P/N A2.23801 V1 V2. This amendment becomes effective November 26, 1969.
2022-08-04: The FAA is adopting a new airworthiness directive (AD) for all Airbus SAS Model A300 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.
94-06-05: 94-06-05 HAMILTON STANDARD: Amendment 39-8853. Docket 94-ANE-09. Applicability: Hamilton Standard Model 14RF-9, 14RF-19, and 14RF-21 propellers, installed on but not limited to Embraer EMB-120 series, Construcciones Aeronauticas, SA (CASA) CN-235 series, and SAAB-SCANIA SF340 series aircraft. Compliance: Required as indicated, unless accomplished previously. To prevent propeller hub cracking and loss of engine oil, and possible loss of a propeller blade or hub, accomplish the following: (a) Within 30 days after the effective date of this airworthiness directive (AD), perform an initial torque check of the propeller hub retaining nuts, as follows: (1) For Hamilton Standard Model 14RF-9 propellers, in accordance with Temporary Revision (TR) No. 61-6, dated March 15, 1993, to Hamilton Standard Maintenance Manual (MM) P5186. (2) For Hamilton Standard Model 14RF-19 propellers, in accordance with TR No. 61-6, dated April 8, 1993, to Hamilton Standard MM P5199. (3) For Hamilton Standard Model 14RF-21 propellers, in accordance with TR No. 61-4, dated March 15, 1993, to Hamilton Standard MM P5189. (b) If propeller hub retaining nuts are found not to meet the acceptance criteria in accordance with the applicable TR to the Hamilton Standard MM's during the initial torque check in accordance with paragraph (a), and during the repetitive torque checks performed in accordance with paragraph (e) of this AD, remove the propeller hub from service and inspect for cracks in accordance with the applicable TR's listed in paragraph (a) of this AD. Remove propeller hubs with crack indications and replace with serviceable propeller hubs prior to further flight. (c) If the initial propeller hub retaining nut torque check is acceptable in accordance with the applicable TR listed in paragraph (a) of this AD, support the propeller with an appropriate lifting fixture and loosen all the propeller hub retaining nuts. Tighten the propeller hub retaining nuts as follows: (1) For Hamilton Standard Model 14RF-9 propellers, in accordance with TR No. 61-7, dated July 27, 1993, to Hamilton Standard MM P5186. (2) For Hamilton Standard Model 14RF-19 propellers, in accordance with TR No. 61-7, dated July 27, 1993, to Hamilton Standard MM P5199. (3) For Hamilton Standard Model 14RF-21 propellers, in accordance with TR No. 61-5, dated July 27, 1993, to Hamilton Standard MM P5189. (d) Make a one-time entry into propeller maintenance records to record: (1) that the initial torque check was performed; (2) the propeller hub retaining nuts were loosened and tightened in accordance with paragraph (c) of this AD; and (3) the torque values. (e) Thereafter, perform repetitive torque checks at intervals not to exceed 500 hours time in service since the last inspection, in accordance with the applicable TR to the Hamilton Standard MM's listed in paragraph (a) of this AD. (f) Install all propellersafter the effective date of this AD using the propeller hub retaining nut tightening procedure defined in the applicable TR to the Hamilton Standard MM's listed in paragraph (c) of this AD. Record the torque values in accordance with paragraph (d) of this AD. (g) Visually inspect and investigate all external propeller oil leakage at the next line check, or within 70 hours TIS after the effective date of this AD, whichever occurs first. If the leakage is found to be caused by other than a leak in the blade seal, the pressure relief valve, or actuator assembly, the propeller must be removed from service and replaced with a serviceable propeller prior to further flight. (h) Thereafter, visually inspect and investigate all external propeller oil leakage at intervals not to exceed 70 hours TIS since the last inspection, or at the next line check, whichever occurs first. If the leakage is found to be caused by other than a leak in the blade seal, the pressure relief valve, or actuator assembly, the propeller must be removed from service and replaced with a serviceable propeller prior to further flight. (i) 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, Boston Aircraft Certification Office. The request should be forwarded through an appropriate FAA Principal Maintenance Inspector, who may add comments and then send it to the Manager, Boston Aircraft Certification Office. NOTE: Information concerning the existence of approved alternative methods of compliance with this airworthiness directive, if any, may be obtained from the Boston Aircraft Certification Office. (j) Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate the aircraft to a location where the requirements of this AD can be accomplished. (k) The torque checks, retightening, and installation procedures shall be done in accordance with the following service documents: Document No. Pages Date TR No. 61-6 to Hamilton Standard MM P5186 1-8 March 15, 1993 Total pages: 8. TR No. 61-7 to Hamilton Standard MM P5186 1-9 July 27, 1993 Total pages: 9. TR No. 61-6 to Hamilton Standard MM P5199 1-6 April 8, 1993 Total pages: 6. TR No. 61-7 to Hamilton Standard MM P5199 1-7 July 27, 1993 Total pages: 7. TR No. 61-4 to Hamilton Standard MM P5189 1-8 March 15, 1993 Total pages: 8. TR No. 61-5 to Hamilton Standard MM P5189 1-7 July 27, 1993 Total pages: 7. 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 Hamilton Standard, One Hamilton Road, Windsor Locks, CT 06096-1010. Copies may be inspected at the FAA, New England Region, Office of the Assistant Chief Counsel, 12 New England Executive Park, Burlington, MA; or at the Office of the Federal Register, 800 North Capitol Street, NW., suite 700, Washington, DC. (l) This amendment becomes effective on March 29, 1994.