Results
69-08-06: 69-08-06 FAIRCHILD: Amdt. 39-750. Applies to All Model F-27 Series and FH-227 Series Airplanes. Compliance required within the next 500 hours time in service after the effective date of this AD unless already accomplished. To prevent hazards associated with an unselected landing gear retraction on the ground, accomplish the following: (a) Rewire the landing gear retraction system in accordance with Fairchild Hiller Service Bulletin 32-64 dated June 12, 1967, for F-27 aircraft and Fairchild Hiller Service Bulletin 32-5 dated March 13, 1967, for FH-227 aircraft or later revision approved by the Chief, Engineering and Manufacturing Branch, FAA, Eastern Region, or equivalent modification approved by the Chief, Engineering and Manufacturing Branch, FAA, Eastern Region. (b) Upon request, with substantiating data submitted through an FAA Maintenance Inspector, compliance time may be increased by the Chief, Engineering and Manufacturing Branch, FAA, Eastern Region.This amendment is effective April 23, 1969.
83-01-02: 83-01-02 GENERAL DYNAMICS (Convair): Amendment 39-4536. Applies to Models 340/440, and military models eligible or to be made eligible for civil use under Type Certificate 6A6, and all such model airplanes converted to turbopropeller power, certificated in all categories. Compliance required as indicated unless previously accomplished. To prevent fracture of the nose landing gear (NLG) axle caused by fatigue cracks, accomplish the following. NOTE: All references to hours of time in service apply to nose landing gear axle and not to the aircraft. (A) Within 150 hours time in service after the effective date of this AD, or prior to the accumulation of 10,150 hours time in service, whichever occurs later, unless accomplished within the last 1050 hours time in service, conduct an ultrasonic inspection of each NLG axle (P/N 240- 5217002 or P/N 340-7310205) in accordance with the applicable provisions of paragraph 2 entitled, "Accomplishment Instructions," of GeneralDynamics Convair Division Service Bulletin 640 (340D) 32-13 dated August 7, 1978. If cracks are found, replace with a like serviceable part prior to return of aircraft to service. (B) Repeat the ultrasonic inspection specified in paragraph (A) or perform the magnetic particle inspection specified in paragraph (C) of this AD at intervals not to exceed 1200 hours time in service. (C) Within 12,000 hours time in service after the effective date of this AD and thereafter at intervals not to exceed 12,000 hours time in service, conduct a magnetic particle inspection of the NLG axle (P/N 240-5217002 or P/N 340-7310205) in accordance with the applicable provisions of paragraph 2, entitled "Accomplishment Instructions" of Service Bulletin 640(340D) 32-13. If cracks are found, replace NLG axle with a like serviceable part prior to return of aircraft to service. (D) Prior to issuance of a Certificate of Airworthiness for military aircraft being converted for civil certification the airplane must be inspected in accordance with paragraph (A) or (C) of this AD. (E) 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 required by this AD. (F) Alternative inspections, modifications or other actions which provide an equivalent level of safety may be used when approved by the Manager, Western Aircraft Certification Field Office, FAA, Northwest Mountain Region, Hawthorne, California. The manufacturer's specifications and procedures identified and described in this directive are incorporated herein and made part hereof pursuant to 5 U.S.C. 552(a)(1). All persons affected by this directive who have not already received these documents from the manufacturer may obtain copies upon request to General Dynamics, Convair Division, P.O. Box 80877, San Diego, California 92138. These documents also may be examined at FAA, Northwest Mountain Region, 17900 Pacific Highway South, Seattle, Washington, or Western Aircraft Certification Field Office, 15000 Aviation Boulevard, Hawthorne, California. This amendment becomes effective January 19, 1983.
2024-18-08: The FAA is adopting a new airworthiness directive (AD) for certain The Boeing Company Model 737-300, -400, and -800 series airplanes. This AD was prompted by a report that the protective spiral wrap used on certain galley wire bundles does not have the correct flammability properties. This AD requires inspecting certain galleys to determine part numbers, inspecting for an existing galley modification placard and marking on galleys with affected part numbers, and replacing wire bundle spiral wrap sleeving as applicable. This AD also prohibits the installation of affected parts. The FAA is issuing this AD to address the unsafe condition on these products.
82-07-02: 82-07-02 CESSNA: Amendment 39-4353. Applies to Models 170A, 170B, 172, 172A through 172P, 175, 175A, 175B, 175C, P172D, and R172E (USAF T-41B) airplanes modified in accordance with STCs SA3-13, SA3-126, SA3-571, SA3-672, SA3-674, SA135CE, SA420CE, SA421CE, SA424CE, SA610SW, SA647CE, SA777CE, SA806CE, SA807CE, or SA1324CE, certificated in any category. \n\n\tCOMPLIANCE: Required as indicated, unless already accomplished. \n\n\tTo reduce the possibility of rapid loss of engine oil caused by ice obstruction of the engine crankcase breather, accomplish the following: \n\n\tA)\tWithin the next 50 hours time-in-service after the effective date of this AD: \n\n\t\t1.\tVisually examine the engine crankcase breather to determine if an alternate air outlet is drilled or cut in the tube as shown in Figure 1. If any of these provisions exist, make an appropriate entry in the aircraft maintenance records per paragraph B). No further action is necessary. \n\n\t\t2.\tIf the hole or cutout shown in Figure 1 is not in the engine crankcase breather tube: \n\n\t\t\ta.\tInspect the crankcase to crankshaft seal and ensure that the seal is secure. (This seal is located behind the starter ring gear in the forward most part of the crankcase.) Reinstall or replace this seal if it is not flush with the forward face of the crankcase. \n\n\t\t\tb.\tDrill the engine crankcase breather tube line to include an alternate air outlet as shown in Figure 1. \n\n\tB)\tParagraph A)1 of this AD may be accomplished by the holder of at least a private pilot certificate issued under Part 61 of the Federal Aviation Regulations on any airplane owned or operated by that person. Make the prescribed entry in the aircraft maintenance records, including those airplanes on which it has already been accomplished, indicating compliance with this AD. \n\n\tC)\tThe airplane may be flown in accordance with FAR 21.197 to a location where paragraph A)2 of this AD may be accomplished. \n\n\tD)\tAny equivalent method of compliance with this AD may be used when approved by the Chief, Wichita Aircraft Certification Office, FAA, Room 238, Mid-Continent Airport, Terminal Building No. 2299, Wichita, Kansas 67209; telephone (316) 269-7000. \n\n\tThis amendment becomes effective on April 8, 1982. \n\nTYPICAL INSTALLATION
2016-16-08: We are adopting a new airworthiness directive (AD) for certain Airbus Model A330-200, -200 Freighter and -300 series airplanes; and Model A340-200 and -300 series airplanes. This AD was prompted by reports of spurious terrain awareness warning system (TAWS) alerts during approach and takeoff for airplanes fitted with the terrain and traffic collision avoidance system with transponder (T3CAS) when the T3CAS is constantly powered ``ON'' for more than 149 hours. This AD requires repetitive on-ground power cycle of the T3CAS. We are issuing this AD to prevent spurious TAWS alerts (collision prediction and alerting (CPA)), or missing legitimate CPA, which could increase flight crew workload during critical landing or takeoff phases, and could possibly result in reduced control of the airplane.
59-17-02: 59-17-02\tBOEING: Applies to all Model 707 Series Aircraft. \n\n\tCompliance required as indicated. \n\n\tSeveral reports have been received concerning the complete or partial disintegration of certain type Purolator, P/N 57737-2 filter elements used in pressure filter assembly BAC P/N F- 18C-12 (Purolator P/N 57726) and in auxiliary return filter, BAC P/N 10-3333-1 (Purolator P/N 64088). \n\n\tThere are two types of filter elements in use having the same P/N 57737-2. They are easily distinguishable by their design. One has a concave bottom plate and the other one a flat bottom together with nonmetallic mesh on the inner surface of the paper convolutions. Investigation has shown that the filter elements which disintegrated were of Purolator concave bottom type supplied prior to July 25, 1959. \n\n\tAlthough all P/N 57737-2 concave bottom type filter elements may not be unsatisfactory, the number and location of unsatisfactory elements is unknown. Accordingly, to eliminate the existent adverse situation, the following must be accomplished. \n\n\t(a)\tAll present inventories of the concave bottom type Purolator filter elements P/N 57737-2 supplied prior to July 25, 1959, must be rejected for any further use in any type certificated aircraft. \n\n\t(b)\tReplacement filter elements in the above noted pressure filter assembly or auxiliary return filter assembly shall utilize either the flat bottom type filter element, P/N 57737-2, or the concave bottom type P/N 57737-2 obtained from Purolator, and dated after July 25, 1959, or other approved replacement filter elements such as Aircraft Porous Media, Inc., P/N ACS-1790E- 12 or Bendix Filter Division, P/N 574615. \n\n\t(Boeing service message dated July 23, 1959, also covers this subject.)
2000-24-23: This amendment adopts a new airworthiness directive (AD) that applies to certain S.N. CENTRAIR 101 series gliders. This AD requires you to inspect the airbrake control system for cracks; and if cracks are detected, replace the airbrake control system. This AD is the result of mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for France. The actions specified in this AD are intended to detect cracks in the airbrake control system and replace cracked parts with parts of improved design. A crack in the airbrake control system could prevent the pilot from using the airbrake system.
2024-19-01: The FAA is adopting a new airworthiness directive (AD) for certain The Boeing Company Model 747-100, 747-100B, 747-100B SUD, 747- 200B, 747-200C, 747-200F, 747-300, 747-400, 747-400D, 747-400F, 747SP, and 747SR series airplanes. This AD was prompted by a report indicating cracks at eight fastener hole locations in the fuselage skin lap splice between certain stations (STAs) at certain stringers. This AD requires repetitive inspections of the upper fastener row of the fuselage skin lap splice in a certain area for any crack, and applicable on-condition actions. The FAA is issuing this AD to address the unsafe condition on these products.
2016-16-06: We are adopting a new airworthiness directive (AD) for certain Airbus Model A300 B4-603, B4-605R, and B4-622R airplanes; and Model A310-304, -324, and -325 airplanes. This AD was prompted by a report of a crack found on door frame (FR) 73A between stringers 24 and 25. This AD requires inspections around the rivet heads of the seal retainer run-out holes at certain frames and corrective actions if necessary. We are issuing this AD to detect and correct cracking of the door frame, which could result in reduced structural integrity of the airplane.
56-17-03: 56-17-03 HARTZELL: Applies to All Model HC-12X20 Reversing Propellers Installed on Downer (Republic) RC-3 Aircraft Having B-55 Valve Assembly. Compliance required as soon as possible but not later than next 25 hours of operation and each 100 hours flight time thereafter. There have been two reported instances of broken valve tube A-57. These failures were due to vibration of the valve assembly and the weakening effect of the valve porthole. Failure of this part will allow the propeller to go into reverse under certain conditions, forcing the airplane to land. In view of the possible serious consequences resulting from inadvertent reversal of the propeller, disassemble the valve and inspect the A-57 valve tube around the valve port with a magnifying glass or with magnetic inspection equipment. If no cracks are found, the sharp edges at the sides of the porthole should be rounded slightly, using a fine round file. This inspection is not required for valve assembly B-299. (Hartzell Service Bulletin No. 38 dated June 16, 1956, covers the same subject.)