Results
2004-25-23: This amendment adopts a new airworthiness directive (AD), applicable to all Boeing Model 747 series airplanes, that requires repetitive inspections for cracking of the top and side panel webs and panel stiffeners of the nose wheel well (NWW), and corrective actions if necessary. This action is necessary to detect and correct fatigue cracks in the top and side panel webs and stiffeners of the NWW, which could compromise the structural integrity of the NWW and could lead to the rapid depressurization of the airplane. This action is intended to address the identified unsafe condition.
2000-23-21: This amendment supersedes emergency airworthiness directive (AD) 2000-08-51. Emergency AD 2000-08-51 was sent to all known U.S. owners and operators of Teledyne Continental Motors (TCM) IO-360, TSIO-360, LTSIO-360, O-470, IO-470, TSIO-470, IO-520, TSIO-520, LTSIO-520, IO-550, TSIO-550, and TSIOL-550 series reciprocating engines by individual letters. This amendment requires removing a core sample of material from the propeller mounting flange of certain crankshafts, and sending the core sample to TCM for evaluation. This amendment is prompted by reports of crankshaft failures, and by the addition of additional crankshaft serial numbers (SN) that have been added to the suspect population. The actions specified by this AD are intended to prevent fracture of the crankshaft connecting rod journal, which could result in total engine power loss, in-flight engine failure and possible forced landing.
2009-07-01: We are adopting a new airworthiness directive (AD) for the products listed above. This AD results from mandatory continuing airworthiness information (MCAI) issued by an aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as: It is necessary to change the limits of the High Pressure (HP) Turbine Stage 1 and Stage 2 Rotor Discs. The maximum approved life of these discs is decreased for all flight missions. This Emergency Airworthiness Directive (EAD) has been raised to instruct mandatory decreased maximum approved lives in the BR715 Time Limits Manual (TLM) T-715-3BR for the HP Turbine Stage 1 Rotor Disc for both Part No. BRH20130 and Part No. BRH20131 and of the High Pressure (HP) Turbine Stage 2 Rotor Disc for both Part No. BRH19423 and Part No. BRH19427 for all flight missions. The life limits are decreased by the same proportion for all flight missions, thus back to birth pro-rata calculations due to the life limit changes are not necessary. We are issuing this AD to prevent rotating parts that may have exceeded their low-cycle fatigue life limits from failing, which could result in uncontained engine failure and subsequent damage to the airplane.
2004-25-21: This amendment adopts a new airworthiness directive (AD), applicable to certain Model EMB-135 and -145 series airplanes. This AD requires modification of the pitch trim system, which includes replacing certain components of the system with new or serviceable components, and upgrading certain software to a newer version. This action is necessary to prevent the temporary loss of the pitch trim command, which could result in reduced controllability of the airplane and consequent injury to the flightcrew and passengers. This action is intended to address the identified unsafe condition.
88-06-04: 88-06-04 BOEING: Amendment 39-5872. Applies to Model 757 series airplanes listed in Boeing Service Bulletin 757-53-0038, dated August 27, 1987, certificated in any category. Compliance required within 18 months after the effective date of this AD, unless previously accomplished. \n\n\tTo prevent structural failure of the vertical fin and horizontal stabilizers in the event of a failure of the aft pressure bulkhead, accomplish the following: \n\n\tA.\tInstall a vertical fin access door and horizontal stabilizer covers in accordance with Boeing Service Bulletin 757-53-0038, dated August 27, 1987, or later FAA-approved revision. \n\n\tB.\tAn alternate means of compliance or adjustment of the compliance time, which provides an acceptable level of safety and which has the concurrence of an FAA Principal Maintenance Inspector, may be used when approved by the Manager, Seattle Aircraft Certification Office, FAA, Northwest Mountain Region. \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\tAll persons affected by this directive who have not already received the appropriate service documents from the manufacturer may obtain copies upon request to the Boeing Commercial Airplane Company, P.O. Box 3707, Seattle, Washington 98124. These documents may be examined at the FAA, Northwest Mountain Region, 17900 Pacific Highway South, Seattle, Washington, or Seattle Aircraft Certification Office, FAA, Northwest Mountain Region, 9010 East Marginal Way South, Seattle, Washington. \n\n\tThis amendment becomes effective April 22, 1988.
2014-11-10: We are superseding Airworthiness Directive (AD) 2008-08-09 for certain Bombardier, Inc. Model CL-600-2B19 (Regional Jet Series 100 & 440) airplanes. AD 2008-08-09 required revising the airworthiness limitations (AWL) section of the Instructions for Continued Airworthiness by incorporating procedures for repetitive functional tests of the pilot input lever of the pitch feel simulator (PFS) units and corrective actions if necessary. This new AD requires replacing certain PFS units with new redesigned PFS units, which would terminate the repetitive functional tests; and both adding and removing certain airplanes from the applicability. This AD was prompted by reports that the shear pin in the input lever of several PFS units failed due to fatigue; and by the development of a re-designed PFS unit, which eliminates the need for repetitive functional tests. We are issuing this AD to prevent undetected failure of the shear pins of both PFS units simultaneously, which could result inloss of pitch feel forces and consequent reduced control of the airplane.
2023-11-03: The FAA is superseding Airworthiness Directive (AD) 2022-18- 03, which applied to certain Honda Aircraft Company LLC (Honda) Model HA-420 airplanes. AD 2022-18-03 required incorporating temporary revisions into the airplane flight manual (AFM) and the quick reference handbook (QRH) that modify procedures for windshield heat operation until the affected windshield assemblies are replaced. This AD retains all actions required by AD 2022-18-03 and corrects typographical errors in certain document numbers specified in certain paragraphs of the regulatory information. The FAA is issuing this AD to address the unsafe condition on these products.
51-20-03: 51-20-03 HILLER: Applies to the following Aircraft: Model UH-12, Serial Numbers 105 to 135, Inclusive. (Incorporating the Collective Pitch Ballast System); Model UH-12A, Serial Numbers 136 to 176, Inclusive, and 178, 180 and 181. Compliance required as noted below. In order to preclude the possibility of protrusion of the bushings from the collective pitch ballast system bracket with resultant reduction of the pitch range of the main rotor blades and restricted controllability, the following should be accomplished: (a) As soon as possible but not later than September 1, 1951, and at each 25-hour inspection period thereafter, visually inspect the collective pitch ballast system bracket P/N 31125-1 for protrusion of either upper or lower bushing P/N 31120-1. Particular inspection should follow each application of grease to the bracket. (b) If the bushing(s) are found to be protruding, the assembly should be reworked by installing set screws in accordance with United Helicopters Mandatory Bulletin No. 19. (c) Inspection of the bracket as specified in part (a) may be discontinued after the rework described in part (b) has been accomplished. (Hiller Helicopters Mandatory Service Bulletin No. 19 covers this same subject.)
2023-08-05: The FAA is adopting a new airworthiness directive (AD) for certain The Boeing Company Model 777 airplanes. This AD was prompted by reports of cracks found in the pivot bulkhead forward outer chord of a certain station. Analysis revealed higher bending stresses across the chord than originally assessed. This AD requires repetitive detailed and high frequency eddy current (HFEC) inspections of the pivot bulkhead forward outer chord of a certain station and longeron fitting for cracking and applicable on-condition actions. The FAA is issuing this AD to address the unsafe condition on these products.
2014-13-11: We are adopting a new airworthiness directive (AD) for all The Boeing Company Model 707 airplanes, and Model 720 and 720B series airplanes. This AD was prompted by reports of scribe-line-related fatigue cracks on Model 727 airplanes, which are similar in design to Model 707 airplanes, and Model 720 and 720B series airplanes. This AD requires inspections for scribe lines in the skin lap joints, external approved repairs, external features, skin butt joints, and decals; and related investigative and corrective actions if necessary. This AD also requires surface finish restoration. We are issuing this AD to detect and correct scribe lines, which can develop into fatigue cracks in the skin and cause rapid decompression of the airplane.