Results
2023-05-08: The FAA is superseding Airworthiness Directive (AD) 2021-04- 05, which applied to certain Airbus Canada Limited Partnership Model BD-500-1A10 and BD-500-1A11 airplanes. AD 2021-04-05 required revising the existing maintenance or inspection program, as applicable, to incorporate new or more restrictive airworthiness limitations. This AD was prompted by a determination that new or more restrictive airworthiness limitations are necessary. This AD continues to require the actions in AD 2021-04-05 and requires revising the existing maintenance or inspection program, as applicable, to incorporate new or more restrictive airworthiness limitations. The FAA is issuing this AD to address the unsafe condition on these products.
89-20-03 R1: 89-20-03 R1 SCHWEIZER AIRCRAFT CORPORATION (HUGHES HELICOPTERS, Inc.): Amendment 39-6540 as revised by Amendment 39-6863. Docket No. 89-ASW-41. Applicability: All Model 269 series helicopters, certified in any category, equipped with 269A6035 series tail rotor blades manufactured before September 15, 1989. Compliance: Required as indicated, unless already accomplished. To prevent the loss of the abrasion strips on the tail rotor blades with subsequent loss of tail rotor control, accomplish the following: (a) Install rivets in the tail rotor blades as follows: (1) Prior to further flight after the effective date of this AD, modify the affected tail rotor blades with the following serial numbers (S/N) in accordance with the procedures detailed in Appendix 1 of this AD: R0056 S524 S584 S640-S644 R0086 S534 S586 S646 R1059 S538 S588 S648-S650 R1066 S539 S589-S594 S653 R1560 S544 S596 S654 R1922 S546 S598-S603 S657 R3296S547 S605 S660-S662 R3314 S549 S607 S664-S666 R3330 S550 S608 S668 R3349 S553 S611-S620 S670-S672 S21 S556-S563 S623-S626 S675-S677 S431 S565 S631-S633 S679-S682 S513 S566 5637 S684-S688 S515 S568-S571 S638 S691-S694 S518 S573 S521 S576-S582 (2) Within the next 100 hours' time in service after the effective date of this AD, modify all tail rotor blades, whether manufactured by Schweizer or Hughes, except those listed in paragraph (a)(1) in accordance with procedures described in Appendix I of this AD. (b) Before the first flight of each day, visually check the abrasion strip of these blades for any evidence of cracking or chipping along the entire abrasion strip/airfoil bond line and the blade tip. (c) If, during the check required by paragraph (b), cracking or chipping is observed, inspect the bond line for bond separation using a 10 power or higher magnifying glass. If evidence of debonding along the abrasion strip/bond line or blade tip is detected, inspect the tail rotor blade using dye penetrant or equivalent inspection method and tap test prior to further flight in accordance with Appendix I of this AD. (d) Remove from service, prior to further flight, any rotor blade found to contain bond separation. (e) The visual check required by paragraph (b) of this AD may be performed by the pilot and must be recorded in accordance with FAR Section 43.9. NOTE: The pilot, when complying, must make appropriate entries and the record must be maintained in accordance with FAR Section 91.173 or 135.439. (f) Aircraft may be ferried in accordance with the provisions of FAR Section 21.197 and 21.199 to a base where the requirements of this AD can be accomplished. (g) Alternative inspections, modifications, or other actions which provide an equivalent level of safety may be used when approved by the Manager, New York Aircraft Certification Office, FAA, 181 South Franklin Avenue, Room 202, Valley Stream, NY. NOTE: Blades modified to Schweizer Installation Instructions No. CKP-C-40, Kit No. SCA-269-K-056, dated August 31, 1989, or Schweizer Service Information Notice No. N- 183.3, September 15, 1989, Part III, comply with paragraph (a) of this AD. (h) Tail rotor blades manufactured by Schweizer with a bond date on or after September 15, 1989, shown on the identification plate located on the inboard end of the blade, are exempt from the requirements of this AD. NOTE: Appendix I, which is not reprinted in this AD, includes material from Schweizer Aircraft Corporation Service Information Notice (S/N) N-183.3, dated September 15, 1989. A copy of the service information may be obtained from Schweizer Aircraft Corporation, P.O. Box 147, Elmira, New York 14902. Airworthiness Directive 89-20-03 R1 supersedes AD 87-22-07, Amendment 39-5730 (52 FR 4155, October 29, 1987). Airworthiness Directive 89-20-03 R1 amends AD 89-20-03, Amendment 39-6540(55 FR 10228, March 20, 1990) which was the Final Rule of Priority Letter AD 89-20-03 issued on September 28, 1990. This amendment (39-6863, AD 89-20-03 R1) becomes effective on February 22, 1991.
2007-26-09: The FAA is superseding an existing airworthiness directive (AD) for all Hartzell Propeller Inc. models ( )HC-( )( )Y( )-( )( )( ) compact series, constant speed or feathering propellers with Hartzell manufactured "Y'' shank aluminum blades. That AD currently requires initial blade inspections, with no repetitive inspections; rework of all "Y'' shank aluminum blades including cold rolling of the blade shank retention radius, blade replacement and modification of pitch change mechanisms for certain propeller models; and changing the airplane operating limitations with specific models of propellers installed. This AD requires the same actions but clarifies certain areas of the compliance, and updates a certain service bulletin (SB) reference to the most recent SB. This AD results from operators requesting clarification of certain portions of AD 2002-09-08. We are issuing this AD to prevent failure of the propeller blade from fatigue cracks in the blade shank radius, which can result in damage to the airplane and loss of airplane control.
2023-04-13: The FAA is superseding Airworthiness Directive (AD) 2021-04- 02, which applied to certain Dassault Aviation Model FALCON 2000EX airplanes. AD 2021-04-02 required revising the existing maintenance or inspection program, as applicable, to incorporate new or more restrictive airworthiness limitations. This AD was prompted by a determination that new or more restrictive airworthiness limitations are necessary. This AD continues to require the actions in AD 2021-04- 02, and also 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 (IBR). The FAA is issuing this AD to address the unsafe condition on these products.
2007-26-04: We are adopting a new airworthiness directive (AD) for certain Boeing Model 737-100, -200, -200C, -300, -400, and -500 series airplanes. This AD requires repetitive detailed and high-frequency eddy current inspections for cracking around the heads of the fasteners on the forward fastener row of certain areas of the station (STA) 259.5 circumferential butt splice, and repair if necessary. This AD also requires a preventive modification, which eliminates the need for the repetitive inspections. This AD results from a report that an operator found multiple cracks in the fuselage skin of a Model 737-200 airplane, at the forward fastener row of the STA 259.5 circumferential butt splice between stringers 19 and 24. We are issuing this AD to prevent cracking of the STA 259.5 circumferential butt splice, which could result in loss of structural integrity of the fuselage skin and possible loss of cabin pressure.
2023-04-15: The FAA is superseding Airworthiness Directive (AD) 2021-09- 12, which applied to certain Dassault Aviation Model FALCON 7X airplanes. AD 2021-09-12 required revising the existing maintenance or inspection program, as applicable, to incorporate new or more restrictive airworthiness limitations. This AD was prompted by a determination that new or more restrictive airworthiness limitations are necessary. This AD continues to require the actions in AD 2021-09- 12 and requires revising the existing maintenance or inspection program, as applicable, to incorporate additional 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.
2007-26-02: We are adopting a new airworthiness directive (AD) for certain Boeing Model 757-200, -200CB, and -300 series airplanes. This AD requires repetitive detailed inspections with a borescope for cracks of the intercostal tee clips; or repetitive detailed inspections for cracks of the intercostal tee clips and attachment fasteners at the number 3 and number 4 doorstops of the passenger door cutouts; and related investigative and corrective actions if necessary. This AD also provides an optional terminating action for the repetitive inspections. This AD results from reports of cracked intercostal tee clips at the number 3 and number 4 doorstops of the passenger door cutouts. We are issuing this AD to detect and correct cracking of the tee clips, which could result in additional stress on the adjacent tee clips, surrounding intercostals, edge frame, door structure and doorstops. This additional stress could cause further cracking or breaking of the tee clips, which could result in failure of the door to seal and consequent rapid decompression of the airplane.
2023-06-10: The FAA is adopting a new airworthiness directive (AD) for all The Boeing Company Model 737-8, -8200, and -9 airplanes. This AD was prompted by a report indicating that certain engine anti-ice (EAI) exhaust duct fasteners were inadequately torqued. This AD requires an inspection or records review to determine the serial number of each engine inlet; and if any affected engine inlet is found, an inspection of the EAI exhaust duct fasteners to determine the gap spacing and if all fasteners are installed, applicable related investigative and corrective actions, and part marking. This AD also limits the installation of affected parts. The FAA is issuing this AD to address the unsafe condition on these products.
2007-25-08: This amendment supersedes an existing airworthiness directive (AD) for the specified Eurocopter France (ECF) model helicopters. That AD currently requires a onetime inspection for end play in the pitch control rod assembly double bearing (bearing) using the tail rotor (T/ R) hub control plate, and before further flight, replacing the bearing if end play is present. This amendment requires checking the T/R gearbox (TGB) oil level before the first flight of the day and maintaining the oil at the maximum level for certain helicopters. Also, this action requires, during each required inspection or at certain specified intervals, ensuring the oil is at the maximum level for certain other model helicopters. This action also requires inspecting the magnetic plug for chips at specified intervals. Depending on the quantity of chips found, this action requires either replacing the TGB before further flight or further inspecting for axial play in the T/R hub pitch change control spider (spider). If axial play is found in the spider, before further flight, this AD requires replacing the bearing. This amendment is prompted by the finding that metal chips were not detected on the magnetic plug due to insufficient oil flow because the oil in the TGB was being maintained at the minimum level. The actions specified by this AD are intended to detect metal chips on the magnetic plug, to prevent damage to the bearing resulting in end play, loss of T/R pitch control, and subsequent loss of control of the helicopter.
2023-05-03: The FAA is superseding Airworthiness Directive (AD) 2022-14- 14, which applied to all Alexander Schleicher GmbH & Co. Segelflugzeugbau Model ASW-15 gliders. AD 2022-14-14 required repetitively inspecting the wing root ribs for cracks, looseness, and damage and replacing any root rib with a crack, a loose rib or lift pin bushing, or any damage. Since the FAA issued AD 2022-14-14, the European Union Aviation Safety Agency (EASA) superseded its mandatory continuing airworthiness information (MCAI) to add all Model ASW-15B gliders to the applicability. This AD is prompted by MCAI originated by an aviation authority of another country to identify and correct an unsafe condition on an aviation product. This AD retains the requirements from AD 2022-14-14 of repetitively inspecting the wing root ribs for cracks, looseness, and damage and replacing any root rib with a crack, a loose rib or lift pin bushing or any damage; and revises the applicability by adding Model ASW-15B gliders and specifying that this AD applies to all Model ASW-15 and ASW-15B gliders equipped with wooden wing root ribs. The FAA is issuing this AD to address the unsafe condition on these products.