Results
2001-20-01: This amendment adopts a new airworthiness directive (AD), applicable to Pratt & Whitney Canada (PWC) PT6A-25C and -114A turboprop engines. This amendment will require initial and repetitive visual inspections, and eventual replacement of the compressor bleed valve assembly, with a redesigned valve assembly for -114A and -25C engines. This amendment is prompted by reports of two occurrences of uncommanded engine power loss. The actions specified by this AD are intended to detect wear in the compressor bleed valve assembly which may cause valve orifice blockage, resulting in a loss of power, an inability to accelerate the engine, and an in-flight shutdown.
2015-17-06: We are adopting a new airworthiness directive (AD) for certain Airbus Model A319, A320, and A321 series airplanes. This AD was prompted by reports that on airplanes equipped [[Page 50552]] with sharklets, discretes (used to activate the load alleviation function) are connected on various flight computers using the same ground point. In these cases, the ground point segregation is no longer effective, and a single failure could lead to loss of sharklet identification by flight computers causing a return to the wing tip fence (no sharklet configuration) performance. This AD requires modification of the sharklet ground connection. We are issuing this AD to prevent loss of sharklet identification by the flight computers and subsequent reduced control of the airplane.
2015-16-07: We are adopting a new airworthiness directive (AD) for REIMS AVIATION S.A. Model F406 airplanes. This AD results from mandatory continuing airworthiness information (MCAI) issued by the aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as detachment of the pilot's rudder control pedal in flight. We are issuing this AD to require actions to address the unsafe condition on these products.
2015-16-01: We are superseding Airworthiness Directive (AD) 2012-19-11 for certain The Boeing Company Model 737 airplanes. AD 2012-19-11 required incorporating design changes to improve the reliability of the cabin altitude warning system by installing a redundant cabin altitude pressure switch, replacing the aural warning module (AWM) with a new or reworked AWM, and changing certain wire bundles or connecting certain previously capped and stowed wires as necessary. For certain airplanes, AD 2012-19-11 also required prior or concurrent incorporation of related design changes by modifying the instrument panels, installing light assemblies, modifying the wire bundles, and installing a new circuit breaker, as necessary. This AD was prompted by the report of a flightcrew not receiving an aural warning during a lack-of-cabin pressurization event. We are issuing this AD to prevent the loss of cabin altitude warning, which could delay flightcrew recognition of a lack of cabin pressurization, andcould result in incapacitation of the flightcrew due to hypoxia (a lack of oxygen in the body), and consequent loss of control of the airplane.
97-23-06: 97-23-06 SCHWEIZER AIRCRAFT CORPORATION: Amendment 39-10194. Docket No. 96-SW-05-AD. Applicability: Model 269A, A-1, B, and C, and TH-55A helicopters, with main rotor transmission ring gear (ring gear), part number (P/N) 269A5104-5, identified by the letters EGC (Eastern Gear Corporation), ACR (ACR Industries), or the manufacturer code number 23751 (EGC) or 57152 (ACR), installed, certificated in any category. NOTE 1: This AD applies to each helicopter identified in the preceding applicability provision, regardless of whether it has been modified, altered, or repaired in the area subject to the requirements of this AD. For helicopters that have been modified, altered, or repaired so that the performance of the requirements of this AD is affected, the owner/operator must use the authority provided in paragraph (f) to request approval from the FAA. This approval may address either no action, if the current configuration eliminates the unsafe condition, or different actions necessary to address the unsafe condition described in this AD. Such a request should include an assessment of the effect of the changed configuration on the unsafe condition addressed by this AD. In no case does the presence of any modification, alteration, or repair remove any helicopter from the applicability of this AD. Compliance: Required as indicated, unless accomplished previously. To prevent failure of the ring gear, loss of drive to the main rotor gearbox, and a subsequent forced landing, accomplish the following: (a) Inspect the ring gear teeth for surface deterioration which includes pitting, excessive wearing, cracking or corrosion in accordance with Schweizer Service Bulletin B-244.2, dated February 19, 1996, as follows: (1) Before further flight, if a clicking or tapping sound or other unusual noise or unusual vibration is detected while operating the helicopter, or if a metal particle is found on the magnetic drain plug during routine maintenance; (2) Beforeinstalling a main rotor transmission which contains an affected ring gear on the helicopter; (3) Within the next 50 hours time-in-service (TIS) after the effective date of this AD, or at the next annual inspection, whichever occurs first. (b) Thereafter, inspect the ring gear teeth at intervals not to exceed 50 hours TIS in accordance with Schweizer Service Bulletin B-244.2, dated February 19, 1996. (c) If surface deterioration which includes pitting, excessive wearing, cracking or corrosion is discovered, before further flight, remove the transmission from service and replace the ring gear with a ring gear, P/N 269A5104-7, serial number (S/N) S2100 or higher number. (d) At the next main rotor transmission overhaul, remove and replace the ring gear, P/N 269A5104-5, identified on the face of the ring gear by the letters EGC, ACR, or the manufacturer code number 23751 (EGC) or 57152 (ACR) and replace it with a ring gear, P/N 269A5104-7, S/N S2100 or higher number. (e) Installation of a ring gear, P/N 269A5104-7, S/N S2100 or higher number constitutes a terminating action for the requirements of this AD and must be annotated on a component log card. A new component log card must be created if a component log card is not in the applicable maintenance records. (f) 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, New York Aircraft Certification Office, FAA. Operators shall submit their requests through an FAA Principal Maintenance Inspector, who may concur or comment and then send it to the Manager, New York Aircraft Certification Office. NOTE 2: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the New York Aircraft Certification Office. (g) Special flight permits may be issued in accordance with sections 21.197 and 21.199 of the Federal Aviation Regulations (14 CFR 21.197 and 21.199) to operate the helicopter to a location where the requirements of this AD can be accomplished, provided no clicking or tapping sound or other unusual noise or unusual vibration was detected on any previous flight. (h) The inspections shall be done in accordance with Schweizer Service Bulletin B-244.2, dated February 19, 1996. 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 Schweizer Aircraft Corporation, P.O. Box 147, Elmira, NY 14902, ATTN: Publications Dept. Copies may be inspected at the FAA, Office of the Regional Counsel, Southwest Region, 2601 Meacham Blvd., Room 663, Fort Worth, Texas; or at the Office of the Federal Register, 800 North Capitol Street, NW., suite 700, Washington, DC. (i) This amendment becomes effective on December 10, 1997.
98-24-14: 98-24-14 CESSNA AIRCRAFT COMPANY: Priority Letter issued on November 13, 1998. Docket No. 98-CE-111-AD. Applicability: The following airplane models and serial numbers, certificated in any category, that are equipped with any WYE tube, P/N 9910299-25 or P/N 9910299-26, in the engine exhaust system: Model Serial Numbers 340A 215 through 1817 414A 1 through 1212 NOTE 1: This AD allows the aircraft owner or pilot to check the maintenance records to determine whether any WYE tube, P/N 9910299-25 or P/N 9910299-26, has been installed in the engine exhaust system since May 1998. See paragraph (c) of this AD for authorization. NOTE 2: Cessna is considering issuing service information pertaining to this subject. This AD takes precedence over any existing or future service information on this subject. NOTE 3: This AD applies to each airplane identified in the preceding applicability provision, regardless of whether it has been modified, altered, or repairedin the area subject to the requirements of this AD. For airplanes that have been modified, altered, or repaired so that the performance of the requirements of this AD is affected, the owner/operator must request approval for an alternative method of compliance in accordance with paragraph (d) of this AD. The request should include an assessment of the effect of the modification, alteration, or repair on the unsafe condition addressed by this AD; and, if the unsafe condition has not been eliminated, the request should include specific proposed actions to address it. Compliance: Required as indicated in the body of this AD, unless already accomplished. To detect and correct exhaust leaks caused by nonwelded exhaust system components, which could result in aluminum fuel lines bursting with consequent fuel spillage, an airplane fire, and/or an explosion, accomplish the following: (a) Prior to further flight after receipt of this priority letter AD, remove from service any P/N 9910299-25 or P/N 9910299-26 engine exhaust system WYE tube. These P/N 9910299-25 or P/N 9910299-26 WYE tubes may be replaced with any of the following in accordance with the instructions in the applicable maintenance manual or other applicable FAA-approved document: (1) P/N 9910299-8 (for the P/N 9910299-25) or P/N 9910299-9 (for the P/N 9910299-26) WYE tubes; or (2) Any other FAA-approved engine exhaust system WYE tube that is not P/N 9910299-25 or P/N 9910299-26. (b) As of the receipt of this priority letter AD, no person shall install, on any affected airplane, any P/N 9910299-25 or P/N 9910299-26 engine exhaust system WYE tube. (c) The owner/operator holding at least a private pilot certificate as authorized by section 43.7 of the Federal Aviation Regulations (14 CFR 43.7) may check the maintenance records to determine whether any WYE tube, P/N 9910299-25 or P/N 9910299-26, has been installed in the engine exhaust system since May 1998. If one of these WYEtubes is not installed, the AD does not apply and the owner/operator must make an entry into the aircraft records showing compliance with this AD in accordance with section 43.9 of the Federal Aviation Regulations (14 CFR 43.9). (d) An alternative method of compliance or adjustment of the compliance times that provides an equivalent level of safety may be approved by the Manager, Wichita Aircraft Certification Office (ACO), 1801 Airport Road, Rm. 100, Mid-Continent Airport, Wichita, Kansas, 67209. The request shall be forwarded through an appropriate FAA Maintenance Inspector, who may add comments and then send it to the Manager, Wichita ACO. NOTE 4: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from Wichita ACO. (e) Information related to this priority letter AD may be examined at the FAA, Central Region, Office of the Regional Counsel, Room 1558, 601 E. 12th Street, Kansas City, Missouri 64106.(f) Priority letter AD 98-24-14, issued November 13, 1998, becomes effective immediately upon receipt.
2015-16-04: We are adopting a new airworthiness directive (AD) for certain Kidde Graviner hand-operated fire extinguishers. This AD was prompted by a report that a fire extinguisher failed to operate when the activation lever was pressed. This AD requires modifying the affected fire extinguishers. We are issuing this AD to prevent fire extinguishers from failing to operate in the event of a fire, which could jeopardize occupants' safety and continuation of safe flight and landing.
99-26-16: This amendment adopts a new airworthiness directive (AD), applicable to certain Bombardier Model CL-600-1A11 (CL-600), CL-600-2A12 (CL-601), and CL-600-2B16 (CL-601-3A, CL-601-3R, and CL-604) series airplanes, that requires, for certain airplanes, removing the hydraulic tube assemblies from the main landing gear (MLG) bay, installing new re-routed hydraulic tube assemblies, and repositioning a fuel line, as applicable. For certain other airplanes, this amendment requires a general visual inspection to determine the routing of certain hydraulic and fuel lines, and repair, if necessary. 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 damage to hydraulic and fuel lines resulting from failure of an MLG, which could cause a fire in the MLG wheel well.
98-08-08: This amendment adopts a new airworthiness directive (AD), applicable to certain Aerospatiale Model ATR42-500 series airplanes. This action requires a one-time inspection to verify the installation of certain stringer clips at the junction of frame 34 and stringer 6, and installation of stringer clips, if necessary. This amendment is prompted by issuance of mandatory continuing airworthiness information by a foreign civil airworthiness authority. The actions specified in this AD are intended to prevent fatigue cracking in the skin of the fuselage, which could result in loss of pressure inside the airplane.
2003-14-21: This amendment supersedes an existing airworthiness directive (AD) that is applicable to Lockheed Martin L-1011-385 series airplanes. That AD currently requires modifications of the engine turbine cooling air overheat monitoring panel at the flight engineer/second officer's console, pilot's caution and warning light panel on the main instrument panel, and the installation of a high speed gearbox (HSGB) overheat detector system into the monitoring system for the engine turbine air temperature. This amendment requires the same modifications. In addition, this amendment adds Lockheed Martin L-1011-385 series airplanes with RB211-22B-02 series engines to the applicability, requires installation of a revised engine front bearing housing assembly, installation of a revised speed probe loom electrical support assembly, and installation of a low pressure (LP) compressor shaft extreme axial movement detector system. Also, this amendment requires additional modifications to the engine turbine cooling air overheat monitoring panel at the flight engineer/second officer's console, pilot's caution and warning light panel on the main instrument panel. The actions specified by this AD are intended to prevent undetected fires originating within the HSGB from breaching the HSGB case, which could result in engine damage and increased difficulty in extinguishing a fire, and to prevent undetected LP compressor shaft location bearing failure, which could result in LP compressor and turbine shaft assembly failure, turbine overspeed, and possible uncontained engine failure.