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74-18-12: 74-18-12 AIRESEARCH MANUFACTURING COMPANY of ARIZONA: Amendment 39-1941. Applies to AiResearch Model TFE 731-2-2B engines installed in, but not limited to Lear-Gates Learjet model 35/36 Aircraft, certificated in all categories. (A) Before further flight, unless previously accomplished, and prior to the installation of replacement fuel control assemblies, replace the hydromechanical fuel control orifice assembly in accordance with AiResearch Alert Service Bulletin TFE 731-A73-3006, dated August 12, 1974, or later FAA approved revisions. (B) Equivalent procedures may be approved by the Chief, Aircraft Engineering Division, FAA Western Region, upon submission of adequate substantiation data. (C) Aircraft may be flown to a base for performance of maintenance required by this AD per FAR's 21.197 and 21.199. This amendment is effective September 3, 1974, for all persons except those to whom it was made effective immediately by telegram dated August 5, 1974.
2012-08-11: We are adopting a new airworthiness directive (AD) for certain Bombardier, Inc. Model DHC-8-400 series airplanes. This AD was prompted by test reports that showed that failure of a retract port flexible hose of a main landing gear (MLG) retraction actuator could cause excessive hydraulic fluid leakage. This AD requires a detailed inspection for defects and damage of the retract port flexible hose on the left and right MLG retraction actuator and replacement of the flexible hose if needed. We are issuing this AD to detect and correct defects and damage of the retract port flexible hose which could lead to an undamped extension of the MLG and could result in MLG structural failure, leading to an unsafe asymmetric landing configuration.
50-41-01: 50-41-01 TAYLORCRAFT: Applies to All Model B Series Aircraft, Serial Numbers 1001 and Up. Compliance required not later than November 15, 1950. Reports have been received of interference between the elevator horn bolt and the fin cover plate apparently caused by improper field installation of the cover plate through bolt. Cases are known where the bolt has worn through the cover plate and such interference may result in jamming of the elevator control system. An inspection of the parts should be made and if evidence of interference is noted, suitable means of preventing the cover plates from interfering with the elevator horn bolt should be incorporated; a spacer bushing at least 1/4 x 0.028 x 1 1/4 inches installed around the cover plate through bolt is considered satisfactory. (Taylorcraft, Inc. Service Bulletin 65 covers this same subject.)
68-11-01: 68-11-01\tBOEING: Amendment 39-605. Applies to Model 707 Series airplanes equipped with Collins Model 51RV-1 navigation receivers and Pratt & Whitney P/N 563586 or General Laboratories P/N 42721 solid state engine ignitor systems. \n\tCompliance required as indicated. \n\tReports indicate a localizer course indicator error may exist when the Pratt & Whitney P/N 563586 or General Laboratories P/N 42721 solid state engine ignitors are turned "ON". Since this unsafe condition is likely to exist in other Boeing Model 707 Series airplanes, the Director determined that: \n\tA.\tFlight operations shall not be predicated on the use of localizer receiver information when engine ignition systems are "ON". \n\tB.\tThe operating limitations specified in subparagraph A of this paragraph must be placed in the aircraft in the form of a placard in clear view of the pilot. For purposes of this AD any documents including a pilot check list including these limitations constitute a placard within the meaningof this paragraph. \n\tC.\tThis limitation does not apply when a 1000 microfarad 50 volt capacitor has been installed across the 28 volt DC input lead to the Collins 51RV-1 receiver in the radio junction box in accordance with Boeing telegraphic Alert Bulletin 2752 dated May 10, 1968, or an equivalent suppression system approved by the Western Region Aircraft Engineering Division. \n\tThis amendment becomes effective on May 31, 1968, for all persons except those to whom it was made effective immediately by telegram dated May 10, 1968.
2012-08-13: We are adopting a new airworthiness directive (AD) for certain The Boeing Company Model 777-200 and -300 series airplanes. This AD was prompted by reports of two failures of the single-tabbed bracket on the rudder. This AD requires replacing certain single-tabbed bonding brackets in the airplane empennage with two-tabbed bonding brackets. This AD also requires, for certain airplanes, installing new bonding jumpers, and measuring the resistance of the modified installation to verify resistance is within specified limits. We are issuing this AD to prevent failure of the bonding jumper bracket, which could result in loss of lightning protection ground path, which could \n\n((Page 24358)) \n\nlead to increased lightning-induced currents and subsequent damage to composite structures, hydraulic tubes, and actuator control electronics. In the event of a lightning strike, loss of lightning ground protection could result in the loss of control of the airplane.
71-19-02: 71-19-02 SOCIETE NATIONAL INDUSTRIELLE AEROSPATIALE (S.N.I.A.S.): Amendment 39-1281. Applies to Sud Model SE.210, MK. V1-R "Caravelle" airplanes. To prevent a possible fire due to unnoticed overheating of a hydraulic system, within the next 500 hours' time in service after the effective date of this AD, unless already accomplished, incorporate S.A. Modification 1262 by installing a Green and Blue Hydraulic System Fluid Overheat Detection System in accordance with Sud Service-Caravelle Bulletin No. 29-70, Revision 10, dated October 12, 1970, or later SGAC-approved issue or an FAA-approved equivalent. This amendment becomes effective September 27, 1971.
68-20-06: 68-20-06 NAVION: Amendment 39-663. Applies to Navion through Navion H airplanes. Compliance required within the next 50 hours time in service after the effective date of this AD, and each annual inspection thereafter. To prevent failure of the Rudder Horn, P/N 145-24401, accomplish the following: Inspect for horizontal cracks or corrosion in the edge of the rudder horn. These cracks would appear as delaminations or swelling under the paint. Replace corroded or cracked rudder horns with new or unused part of the same part number or Federal Aviation Administration approved equivalent part before further flight. This amendment becomes effective October 3, 1968.
67-15-03: 67-15-03 ROLLS-ROYCE: Amdt. 39-399 Part 39 Federal Register April 14, 1967. Applies to All Dart Series 525, 526, 527, 528, 529, 531, and 532-7 Series Engines with Rolls-Royce Modification 529 (Part 2) Bearing in the Rear Position. Compliance required as indicated. (a) Inspect the oil filter on all Dart 525, 526, 527, 528, 529, 531, and 532-7 Series engines modified in accordance with Rolls-Royce Modification 529 Part 2 Standard at the following times: (1) Within 25 hours' time in service after the effective date of this AD, unless already accomplished within the last 25 hours, and thereafter at intervals not exceeding 50 hours' time in service from the last inspection; and (2) Before further flight, when an increase in oil consumption or a drop in oil pressure is reported. (b) If metal particles are found in the filters, remove the engine from service and further inspect to determine whether repairs are required. (c) If the inspection in (b) indicates that repairs are required, modify the rear bearing in accordance with Rolls Royce Dart Service Bulletin No. Da. 72-232, by implementing any of the following modifications as applicable (1) Mod. 1023, Mod. 1030 and DRS. 411; (2) Mod. 1106 or Mod. 1109; or (3) Mod. 1167. (d) Upon request of the operator, an FAA maintenance inspector, subject to prior approval of the Chief, Aircraft Certification Staff, Europe, Africa and Middle East Region, may adjust the repetitive inspection intervals specified in this AD to permit compliance at an established inspection period of the operator if the request contains substantiating data to justify the increase for such operator. This supersedes AD 63-21-7. This directive effective May 14, 1967.
2012-07-06: We are adopting a new airworthiness directive (AD) for certain The Boeing Company Model 777 airplanes. This AD was prompted by a new revision to the airworthiness limitations of the maintenance planning document. This AD requires revising the maintenance program to update inspection requirements to detect fatigue cracking of principal structural elements (PSEs). We are issuing this AD to ensure that fatigue cracking of various PSEs is detected and corrected; such fatigue cracking could adversely affect the structural integrity of these airplanes.
75-05-10: 75-05-10 BOEING: Amendment 39-2107. Applies to Boeing Model 727-200 series airplanes certificated in all categories, and Boeing Model 727-100, Serial Numbers 18877, 18878, 18879, 19281 and 19279 only. Compliance required as indicated. \n\tTo prevent escape slide latch cable failure and ensuing inability to open emergency exit and deploy escape slide, accomplish the following: \n\tA.\tWithin 25 hours time in service after effective date of this AD, unless already accomplished, inspect door mounted escape slide latch cable at both entry and service doors (4 doors). If corrosion or breakage is found, replace prior to further flight with a carbon steel assembly of the same type design and reinspect at intervals not to exceed 500 hours time in service, or replace with corrosion resistant assembly, per Boeing Alert Service Bulletin 727-25- 223, or later FAA approved revisions, or replace in a manner approved by the Chief, Engineering and Manufacturing Branch, FAA Northwest Region. \n\tB.\tBySeptember 1, 1975, unless already accomplished, replace carbon steel cable assembly with corrosion resistant assembly per Boeing Alert Service Bulletin 727-25-223, or later FAA approved revisions, or in a manner approved by the Chief, Engineering and Manufacturing Branch, FAA Northwest Region. \n\tThe manufacturer's specifications and procedures identified and described in this directive are incorporated herein and made a part hereof pursuant to 5 U.S.C. 552(a)(1). \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. The documents may also be examined at FAA Northwest Region, 9010 East Marginal Way South, Seattle, Washington. \n\n\tThis amendment becomes effective March 25, 1975.