Results
94-22-05: This amendment adopts a new airworthiness directive (AD), applicable to certain Fokker Model F28 Mark 0100 series airplanes, that requires inspections to detect cracks of certain demountable flange (inboard) wheel subassemblies and of the bolt bosses on certain demountable flange (outboard) wheel subassemblies, and modification or replacement of the wheel subassemblies. This amendment is prompted by reports of cracks and broken spokes found on certain main wheel assemblies of these airplanes. The actions specified by this AD are intended to prevent loss of a main wheel assembly during takeoff or landing.
2022-02-15: The FAA is superseding Airworthiness Directive (AD) 2020-12-06 for all Gulfstream Aerospace Corporation (Gulfstream) Model G-IV airplanes. AD 2020-12-06 required replacing the nose wheel steering servo valve manifold, incorporating revised operating procedures into the airplane flight manual (AFM), doing a records inspection for any incidents of un-commanded nose wheel steering turns, and reporting the results to the FAA. Since the FAA issued AD 2020-12-16, the FAA determined that a typographical error was made in citing one of the AFM documents. This AD retains the actions of AD 2020-12-06 and corrects the citation to the AFM. The FAA is issuing this AD to address the unsafe condition on these products.
88-03-06: 88-03-06 TELEDYNE CONTINENTAL MOTORS (TCM): Amendment 39-5888. Applies to IO-360, TSIO-360, O-470, IO-470, TSIO-470, IO-520, TSIO-520, GTSIO-520, and IO-550 series engines equipped with oil filters. Compliance is required at the next oil change or within 10 flight hours, whichever occurs first, unless already accomplished. To prevent possible loss of engine oil and subsequent engine failure, accomplish the following: (a) Determine if oil filter TCM P/N 649309 or 649310 is installed. (1) If neither filter is installed, proceed to paragraph (b). (2) If P/N 649309 is installed, replace with P/N 649923 or equivalent Parts Manufacturer Approval (PMA) product. (3) If P/N 649310 is installed, replace with P/N 649922 or equivalent PMA product. (b) Make appropriate log book entry showing compliance with this AD. (c) Aircraft may be ferried in accordance with the provisions of Federal Aviation Regulations 21.197 and 21.199 to a base where this AD can be accomplished. (d) Upon request, an equivalent means of compliance with the requirements of this AD may be approved by the Manager, Atlanta Aircraft Certification Office, Federal Aviation Administration, 1669 Phoenix Parkway, Suite 210C, Atlanta, Georgia 30349. (e) Upon submission of substantiating data by an owner or operator, through an FAA maintenance inspector, the Manager, Atlanta Aircraft Certification Office, may adjust the compliance time specified in this AD. NOTES: (1) TCM Service Bulletin No. M88-4, dated January 15, 1988, refers to this subject. (2) TCM oil filter P/N's 649309 and 649310, in inventory, should be returned to TCM in accordance with the TCM service bulletin referenced in Note 1. This amendment, 39-5888, becomes effective April 15, 1988, as to all persons except those persons to whom it was made immediately effective by individual priority letter AD 88-03-06, issued February 5, 1988, which contained this amendment.
99-01-03: This amendment supersedes Airworthiness Directive (AD) 97-14- 16, which applies to Raytheon Aircraft Company (Raytheon) Models 1900, 1900C, and 1900D airplanes. AD 97-14-16 currently requires repetitively inspecting the outboard flap support roller bearings and flap attachment brackets for indications of contact (wear), inspecting for elongated holes in the flap attachment brackets, repairing or replacing any part showing wear, and replacing any bracket with elongated holes. AD 97-14-16 was the result of five incidents where the flap roller bearings rubbed on the flap attachment brackets and resulted in aileron interference. This AD retains the repetitive inspection requirement of AD 97-14-16, but reduces the number of ground-air-ground (GAG) cycles allowed between inspections and lowers the total number of accumulated GAG cycles allowed before mandatory accomplishment of the initial inspection. This AD also provides the option of replacing the outboard flap roller bearings with parts of improved design as terminating action for the repetitive inspection requirement. The actions specified by this AD are intended to prevent asymmetric flaps, jammed flaps, and/ or possible interference between the flap and the aileron, which could inhibit aileron travel and result in possible loss of roll control of the airplane.
65-15-03: 65-15-03 CONSOLIDATED AERONAUTICS: Amdt. 39-103 Part 39 Federal Register July 1, 1965. Applies to Model Lake LA-4 Aircraft. Compliance required within the next 25 hours' time in service after the effective date of this AD unless already accomplished. To prevent failure of the nose landing gear to latch in the down and locked position, accomplish the following: (a) Inspect the bolt at the top of the nose gear drag strut at Fuselage Station 12 5/8 that connects the upper drag strut assembly, Lake P/N 2-4411-1, to the support assembly plates, Lake P/N 2-4412-27, to ensure that an AN5-16A bolt or an FAA-approved equivalent is installed and that the bolt head is on the right-hand side of the aircraft. (b) If an AN5-15A bolt is installed, remove the bolt and visually inspect the bolt hole of the upper drag strut assembly and both support assembly plates for elongation. (c) Rework any part having an elongated bolt hole in accordance with Consolidated Aeronautics, Inc., Lake Aircraft Division, Service Letter No. 11B, dated February 22, 1965, or an equivalent approved by the Chief, Engineering and Manufacturing Branch, FAA Eastern Region, or replace the part with a new part of the same part number or an equivalent approved by the Chief, Engineering and Manufacturing Branch, FAA Eastern Region. (d) Replace any AN5-15A bolt with an AN5-16A bolt or an AN5-17A bolt as necessary when bushings are installed or an FAA-approved equivalent, installing the bolt with the head on the right-hand side of the aircraft. (e) Reverse any AN5-16A bolt that is installed with the head on the left-hand side of the aircraft. This directive effective July 1, 1965.
2021-26-25: The FAA is adopting a new airworthiness directive (AD) for certain Schempp-Hirth Flugzeugbau GmbH Model Duo Discus and Duo Discus T gliders. This AD was prompted by mandatory continuing airworthiness information (MCAI) originated 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 jerky extension of the air brakes at very high air speeds, including cases where the air brake blades interlock. This AD requires replacing certain air brake end stop bushings, inspecting certain other air brake end stops, and repairing if necessary. The FAA is issuing this AD to address the unsafe condition on these products.
2022-02-16: The FAA is adopting a new airworthiness directive (AD) for all The Boeing Company Model 787-8, 787-9, and 787-10 airplanes. This AD was prompted by a determination that radio altimeters cannot be relied upon to perform their intended function if they experience interference from wireless broadband operations in the 3.7-3.98 GHz frequency band (5G C-Band), and a recent determination that, during landings, as a result of this interference, certain airplane systems may not properly transition from AIR to GROUND mode when landing on certain runways, resulting in degraded deceleration performance and longer landing distance than normal due to the effect on thrust reverser deployment, speedbrake deployment, and increased idle thrust. This AD requires revising the limitations and operating procedures sections of the existing airplane flight manual (AFM) to incorporate limitations prohibiting certain landings and the use of certain minimum equipment list (MEL) items, and to incorporate operating procedures for calculating landing distances, when in the presence of 5G C-Band interference as identified by Notices to Air Missions (NOTAMs). The FAA is issuing this AD to address the unsafe condition on these products.
89-14-07: 89-14-07 AEROSPATIALE: Amendment 39-6257. Applicability: Model ATR42-300 series airplanes, Serial Numbers 003 through 052, certificated in any category. Compliance: Required as indicated, unless previously accomplished. To prevent failure of the emergency exit frame, accomplish the following: A. Prior to the accumulation of 12,000 landings or within 60 days after the effective date of this AD, whichever occurs later, accomplish modification of the fuselage emergency exit frame in accordance with Aerospatiale Service Bulletin ATR42-53-0024, Revision 2, dated May 16, 1988. B. An 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, Standardization Branch, ANM-113, FAA, Northwest Mountain Region. NOTE: The request should be forwarded through an FAA Principal Maintenance Inspector (PMI), who will either concur or comment and then send it to the Manager, Standardization Branch, ANM-113. C. Special 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. All persons affected by this directive who have not already received the appropriate service documents from the manufacturer may obtain copies upon request to Aerospatiale, 316 Route de Bayonne, 31060 Toulouse, Cedex 03, France. These documents may be examined at the FAA, Northwest Mountain Region, Transport Airplane Directorate, 17900 Pacific Highway South, Seattle, Washington, or at the Standardization Branch, 9010 East Marginal Way South, Seattle, Washington. This amendment (39-6257, AD 89-14-07) becomes effective on August 7, 1989.
47-36-02: 47-36-02 DOUGLAS: (Was Mandatory Note 2 of AD-3L-1.) Applies to A-26B and A-26C Aircraft. Compliance required prior to operation in cold weather and not later than next engine overhaul. To preclude collapse of the oil screen during cold weather starting, replace oil screen assembly No. 51887 with oil screen assembly Nos. 51887M or 107547. P/N 51887 may be reworked to P/N 51887M by incorporating reinforcing spring No. 107542 and adding the letter "M" to the part number.
2004-13-17: This amendment supersedes an existing airworthiness directive (AD), applicable to certain Fokker Model F.28 Mark 0070 series airplanes, that currently requires a one-time inspection to detect loose bolts attaching the gustlock counter-bracket to the pulley on the elevator tension regulator (control) assembly, and corrective action if necessary. This AD instead requires a modification of the elevator tension control mechanism. This AD also revises the applicability to include additional airplanes. The actions specified by this AD are intended to prevent restricted elevator movement and consequent reduced controllability of the airplane. This AD is intended to address the identified unsafe condition.