Results
2018-07-12: We are adopting a new airworthiness directive (AD) for all Airbus Model A350-941 airplanes. This AD requires performing repetitive station position pick-off unit (SPPU) calibration tests, and applying the corresponding airplane fault isolation if necessary. This AD was prompted by a report indicating malfunctions of the SPPU and failures of the internal wiring due to water ingress via certain electrical connectors, inducing subsequent icing during flight. We are issuing this AD to address the unsafe condition on these products.
85-12-07: 85-12-07 FOKKER: Amendment 39-5080. Applies to Model F27 series airplanes, serial numbers 10105 through 10648, 10654, 10658 through 10660, 10662 through 10667 and 10669 through 10672, certificated in all categories. To ensure structural integrity of the rudder tab, accomplish the following, unless already accomplished: A. Conduct a one-time visual inspection of the rudder tab in accordance with Fokker Service Bulletin F27/55-58, dated March 28, 1985, within twenty days after the effective date of this AD. B. If incorrect rivets are found, repair the tab before further flight in accordance with the above service bulletin or in a manner approved by the Manager, Seattle Aircraft Certification Office. C. Alternate means of compliance which provide an acceptable level of safety may be used when approved by the Manager, Seattle Aircraft Certification Office, FAA, Northwest Mountain Region. D. Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate airplanes to a base for the accomplishment of inspections and/or modifications required by this AD. All persons affected by this directive who have not already received these documents from the manufacturer may obtain copies upon request to Fokker B.V., Product Support, P.O. Box 7600, 11172J Schiphol Oost, The Netherlands. These documents also may be examined at FAA Northwest Mountain Region, 17900 Pacific Highway South, Seattle, Washington, or Seattle Aircraft Certification Office, 9010 East Marginal Way South, Seattle, Washington. This amendment becomes effective June 28, 1985.
2005-13-10: The FAA adopts a new airworthiness directive (AD) for certain Cessna Aircraft Company (Cessna) Models 172R, 172S, 182T, T182T, 206H, and T206H airplanes. This AD requires you to inspect any MC01-3A I.C. 9 or MC01-3A I.C. 10 main electrical power junction box circuit breakers for correct amperage (amp) (a correct 40-amp circuit breaker) and replace any incorrect amp circuit breaker with the correct 40-amp circuit breaker. This AD results from several reports of circuit breakers that are not the correct 40-amp circuit breaker installed in the MC01-3A main electrical power junction box. We are issuing this AD to replace any incorrect circuit breaker installed in the MC01-3A I.C. 9 or MC01-3A I.C. 10 main electrical power junction box, which could result in premature tripping of the power junction box main feeder circuit breakers and could lead to partial or complete loss of all electrical power on the airplane. This condition could lead to the loss of all navigation and communication equipment and lighting in the cockpit.
2005-13-09: The FAA adopts a new airworthiness directive (AD) for certain GROB-WERKE Model G120A airplanes. This AD requires you to replace the main landing gear (MLG) up-lock hook assembly. This AD results from mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for Germany. We are issuing this AD to prevent the MLG from becoming jammed and not extending, which could result in loss of control of the airplane during landing. During the comment period for the notice of proposed rulemaking (NPRM) regarding this action, we received a comment recommending the incorporation of service information to install connecting bolts secured with cotter pins instead of connecting bolts secured with snap rings. All U.S.- registered airplanes currently have these actions incorporated so these actions do not impose an additional burden over that proposed in the NPRM and prior public comment is not necessary. However, we are reopening the comment period to allow the public the chance to comment on these additional actions.
62-19-03: 62-19-03 PIPER: Amdt. 478 Part 507 Federal Register August 23, 1962. Applies to All Model PA-28 Aircraft, Serial Numbers 28-1 to 28-314 Inclusive, 28-317 to 28-326 Inclusive, 28- 328 to 28-331 Inclusive, 28-333 to 28-341 Inclusive, 28-343, 28-345 to 28-348 Inclusive, 28- 351, 28-352, 28-356, 28-359, and 28-365. Compliance required as indicated. There has been inflight failure of the propeller attach bolts due to under-torquing of the bolts. In order to preclude the loss of the propeller due to the failure of the bolts, the following is required: (a) Within the next 10 hours' time in service after the effective date of this AD, unless already accomplished, remove the propeller spinner and remove each propeller attach bolt. (b) Inspect for cracks in the bolt in the area of the threads using magnetic particle or FAA-approved equivalent inspection method in conjunction with a 5-power or higher magnifying glass. Inspect the grip shank for brinelled surfaces with a5-power or higher magnifying glass. (c) If cracks are found or if the bolt is brinelled on the grip shank, replace with new bolts, AN 76-41S. Torque to 300 inch-pounds. (d) If cracks are not found, reinstall the bolts and torque to 300 inch-pounds. (e) In lieu of the inspection requirement of (b), new bolts, AN 76-41S, may be installed and torqued to 300 inch-pounds. (Piper Service Bulletin No. 209, dated April 17, 1962, covers this same subject.) This directive effective August 28, 1962.
2018-07-07: We are adopting a new airworthiness directive (AD) for all Dassault Aviation Model FAN JET FALCON, FAN JET FALCON SERIES D, E, F, and G airplanes; and certain Model MYSTERE-FALCON 20-C5, 20-D5, 20-E5, and 20-F5 airplanes. This AD was prompted by reports of the collapse of the main landing gear (MLG) on touchdown. This AD requires an electrical modification of the landing gear sequence logic. We are issuing this AD to address the unsafe condition on these products.
86-07-11: 86-07-11 BOEING: Amendment 39-5285. Applies to Boeing Model 757 airplanes, line numbers 1 through 90, certificated in any category. Compliance is required within 30 days after the effective date of this amendment. To ensure proper door opening, accomplish the following, unless already accomplished: \n\n\tA.\tInspect the left and right side Number 1, 2, and 4 passenger doors to verify proper engagement of the upper pinch bolt, and reinstall, if necessary, in accordance with Boeing Service Bulletin 757-52A0019, dated February 27, 1986, or later FAA-approved revisions. \n\n\tB.\tAlternate means of compliance or adjustment of compliance time, which provides an acceptable level of safety, 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 for the accomplishment of inspections and/or modifications required by this AD. \n\n\tAll persons affected by this AD who have not already received copies of the service bulletin cited herein may obtain copies upon request from the Boeing Commercial Airplane Company, P.O. Box 3707, Seattle, Washington 98124. This document may be examined at the FAA, Northwest Mountain Region, 17900 Pacific Highway South, Seattle, Washington, or the Seattle Aircraft Certification Office, 9010 East Marginal Way South, Seattle, Washington. \n\n\tThis amendment becomes effective April 28, 1986.
62-17-04: 62-17-04 EDO: Amendment 473 Part 507 Federal Register August 4, 1962. Applies to Model 249A2870 (A Model Only) Float Installations, Float Serial Numbers 1 to 280, Installed on Cessna Model 180 Series Per STC SA1-622 and Cessna Model 185 Seaplanes. Compliance required within the next 5 hours' time in service after the effective date of this AD, unless already accomplished. Longitudinal cracks have been found on Edo streamlined struts P/N 6061T6, in the area near the 30 and 60 percent chord sections. To preclude operations with defective struts accomplish the following: Visually inspect each side of the full length of the attachment strut, P/N 6061T6, for longitudinal cracks. Replace cracked struts prior to further flight. NOTE: Report the details on any defective struts found to the FAA Engineering and Manufacturing Branch, ATTN: EA-212, Hangar 18, Room 210, New York International Airport, Jamaica 30, New York. (Edo telegram of July 7, and Edo letter ofJuly 9, 1962, cover the same subject.) This directive effective August 14, 1962.
84-23-05: 84-23-05 BOEING: Amendment 39-4949. Applies to Boeing Model 737 series airplanes, certificated in all categories, listed in Boeing Service Bulletin 737-55A1029, Revision 3. To ensure continued structural integrity of the horizontal stabilizer, accomplish the following, unless previously accomplished: \n\n\tA.\tInspect the rear spar horizontal stabilizer attach lugs for cracks in accordance with instructions in Boeing Service Bulletin 737-55A1029, Revision 3, or later FAA approved revision, upon the accumulation of the threshold number of landings specified in Table I of the service bulletin or within 200 landings after the effective date of this AD, whichever occurs later. Repeat these inspections at intervals not exceeding those specified in Table I of the service bulletin. \n\n\tB.\tCracked parts must be replaced or repaired in a manner approved by the Manager, Seattle Aircraft Certification Office, FAA, Northwest Mountain Region before further flight. \n\n\tC.\tAirplanes may be flown to a maintenance base for repairs or replacement in accordance with FAR 21.197 and 21.199 with prior approval of the Manager, Seattle Aircraft Certification Office, FAA, Northwest Mountain Region. \n\n\tD.\tFor purposes of complying with the AD, subject to the acceptance by the assigned FAA Maintenance Inspector, the number of landings may be determined by dividing each airplane's hours time in service by the operator's fleet average time from takeoff to landing for the airplane type. \n\n\tE.\tAlternate means of compliance which provide an equivalent level of safety may be used when approved by the Manager, Seattle Aircraft Certification Office, FAA, Northwest Mountain Region. \n\n\tF.\tUpon request by the operator, an FAA Principal Maintenance Inspector, subject to prior approval by the Manager, Seattle Aircraft Certification Office, FAA, Northwest Mountain Region, may adjust the repetitive inspection interval in this AD, if the request contains substantiating data to justify the increase for the operator. \n\n\tAll persons affected by this directive who have not already received these documents from the manufacturer may obtain copies upon request to Boeing Commercial Airplane Company, P.O. Box 3707, Seattle, Washington 98124. These documents may also be examined at the FAA, Northwest Mountain Region, 9010 East Marginal Way South, Seattle, Washington. \n\n\tThis supersedes Amendment 39-4122 (46 FR 28147; May 26, 1981), AD 81-11-07. \n\tThis Amendment 39-4949 becomes effective December 15, 1984.
62-13-01: 62-13-01 ANDREA RADIO CORPORATION: Amdt. 447. Part 507 Federal Register June 1, 1962. Applies to All Aircraft Equipped With Intercommunication Sets Models AN/AIC-10A and AN/AIC-18(A-81), Except Those With Control Panel Serial Number 332 and Subsequent. Compliance required as indicated. Within the next 200 hours' time in service after the effective date of this airworthiness directive unless already accomplished, modify Model AN/AIC-18(A-81) in accordance with Andrea Radio Corporation Field Modification C41-5115 and Model AN/AIC-10A in accordance with Andrea Radio Corporation Field Modification C41-5116, so that the adjustable attenuation range does not exceed 10 decibels. When the modification has been completed add marking "MOD" adjacent to the TSO-C50 label. Within the next 10 hours' time in service after the effective date of this airworthiness directive unless already accomplished, as an interim procedure pending modification, install a placard requiring that the master level control on the isolation amplifier be full "ON" at any time range problems are being worked. (Andrea Radio Corporation Field Modification C41-5115 for AN/AIC-18(A-81) and C41-5116 for the AN/AIC-10A, both dated April 5, 1962, cover this same subject.) This directive effective June 1, 1962.