Results
2023-06-04: The FAA is adopting a new airworthiness directive (AD) for certain Bombardier, Inc., Model CL-600-1A11 (600), CL-600-2A12 (601), and CL-600-2B16 (601-3A, 601-3R, and 604 Variants) airplanes. This AD was prompted by reports of some passenger oxygen mask dispensing units (MDUs) with lanyards that are too long to meet the proper length specifications of the airplane. This AD requires replacing the affected MDUs with units that meet the proper length specifications, replacing the placards, and re-identifying the assemblies. The FAA is issuing this AD to address the unsafe condition on these products.
2023-06-09: The FAA is adopting a new airworthiness directive (AD) for certain Gulfstream Aerospace LP Model Galaxy airplanes and Model Gulfstream 200 airplanes. This AD was prompted by reports that wing flap fairing debonding and corrosion were discovered at certain areas of the lower skin on both wings. This AD requires an inspection for corrosion in certain areas of the wing skin fairings, additional inspections if necessary, resealing the fairings with new fillet seal, and applicable corrective actions, as specified in a Civil Aviation Authority of Israel (CAAI) AD, which is incorporated by reference. The FAA is issuing this AD to address the unsafe condition on these products.
2007-26-07: The FAA is adopting a new airworthiness directive (AD) for certain Boeing Model 747-200B, 747-300, 747-400, 747-400D, and 747-400F series airplanes. This AD requires repetitive inspections of the left- and right-hand flipper door assemblies of the engine core cowls for migrated pins and damaged flipper doors, and corrective actions if necessary. Modification of the hinge assemblies terminates the repetitive inspections. This AD results from two reports of missing flipper doors for the engine core cowls. We are issuing this AD to detect and correct migrated hinge pins and damaged flipper doors, which could allow the flipper door to fall off, resulting in the potential for an engine fire to propagate into the flammable leakage zone of the strut and for the amount of fire extinguishing agent reaching the fire to be diluted, and subsequent uncontained fire in the engine strut.
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.