Results
2020-24-08: The FAA is adopting a new airworthiness directive (AD) for certain Rolls-Royce Deutschland Ltd & Co KG (Type Certificate Previously Held by Rolls-Royce plc) (RRD) RB211 Trent 768-60, 772-60, 772B-60 and 772C-60 model turbofan engines. This AD requires replacement of high-pressure turbine (HPT) blades with parts eligible for installation before exceeding specified flight cycles since new. This AD was prompted by several reports from the manufacturer that HPT blades on RB211 Trent 700 model turbofan engines have been subject to high levels of corrosion fatigue, leading to blade cracking and eventual release, resulting in an aborted take-off and in-flight shut- downs. The FAA is issuing this AD to address the unsafe condition on these products.
78-22-06: 78-22-06 GULFSTREAM AMERICAN CORPORATION (GAC): Amendment 39- 3331. Applies to GAC Model GA-7 serial numbers GA7-0002 through GA7-0036, GA7-0038 through GA7-0043, GA7-0045, GA7-0046, and GA7-0049, airplanes certificated in all categories. Compliance is required as indicated, unless already accomplished. To prevent failure of the elevator trim control master chain and loss of elevator trim control, accomplish the following within 5 flight hours of the effective date of this AD: Inspect and modify the elevator trim control system in accordance with GAC Service Bulletin ME-6 dated October 18, 1978, or later revision approved by the Chief, Engineering and Manufacturing Branch, FAA, Southern Region, or in an equivalent manner approved by the Chief, Engineering and Manufacturing Branch, FAA, Southern Region. The inspection and/or alteration required by this AD constitute maintenance and may be performed by persons authorized to perform such maintenance under FAR 43.This amendment becomes effective November 2, 1978.
2004-01-08: This amendment adopts a new airworthiness directive (AD) that applies to Pratt & Whitney (PW) JT9D-7R4 series turbofan engines. This amendment requires on JT9D-7R4 series turbofan engines with steel fan cases, replacement of the existing one-piece fan case shield with a thicker four-piece fan case shield and would add four fan case shield supports. This amendment results from two uncontained full fan blade fracture events that resulted in penetration of the steel fan case and fan case shield. We are issuing this AD to prevent uncontained fan blade failures, resulting in damage to the airplane.
95-01-04: This amendment adopts a new airworthiness directive (AD) that is applicable to certain Boeing Model 747-100 series airplanes. This action requires an inspection to detect discrepancies of the lap joint in certain fuselage stations, repair of any discrepancies, and modification of a certain lap joint. This amendment is prompted by reports of holes in the lap joints and longerons of these airplanes. The actions specified in this AD are intended to prevent reduced fatigue life of the fuselage in the areas in which holes are found.
2020-24-10: The FAA is adopting a new airworthiness directive (AD) for all Aerostar Aircraft Corporation (Aerostar) Model PA-60-601P (Aerostar 601P), PA-60-602P (Aerostar 602P), and PA-60-700P (Aerostar 700P) airplanes. This AD was prompted by reports of corrosion on the elevator and aileron balance tubes. This AD requires repetitively inspecting the elevator and aileron balance tubes for corrosion and rust and replacing the tube. The FAA is issuing this AD to address the unsafe condition on these products.
76-17-03: 76-17-03 GRUMMAN AMERICAN AVIATION CORPORATION: Amendment 39- 2699. Applies to Model Serial Number AA1, AA1A 0001 and up AA1B 0001 thru 0641 AA5 0001 and up AA-5A 0001 thru 0173, 0176 thru 0196 AA-5B 0001 thru 0309, 0311 thru 0324 airplanes certificated in all categories. Compliance required within the next 25 flight hours' time in service after the effective date of this AD, unless already accomplished. To detect delaminations in bonded skins and prevent any possible further delaminations, accomplish the following: Inspect and perform rework as prescribed by the instructions of Grumman American Aviation Corporation Service Bulletin No. 155, dated July 30, 1976, or an equivalent inspection and modification approved by the Chief, Engineering and Manufacturing Branch, Great Lakes Region. This amendment becomes effective August 30, 1976.
77-24-02: 77-24-02 SHORT BROTHERS AND HARLAND, LTD: Amendment 39-3080. Applies to SC 7 Series 3 airplanes except those modified in accordance with Shorts Modification No. 1658. Compliance is required as indicated. To detect cracks and prevent possible failure of the flap mechanism support structure, accomplish the following: (a) Before the accumulation of 5,000 landings or within 10 hours time in service after the effective date of this AD, whichever occurs later, unless already accomplished, visually inspect the flap mechanism support structure using a 10 power magnifying glass, for cracking and evidence of chafing and inadequate clearances in accordance with Part A, Steps 1 through 3, of Shorts Alert Service Bulletin No. 27-A64, Revision 3, dated September 7, 1977, (service bulletin) or an FAA-approved equivalent. (1) If cracks are found during any inspections required by this AD, that are within the acceptable limits shown in Figures 1 and 2 of the service bulletin, reinspect the flap mechanism support structure prior to each day's operation in accordance with paragraph (a) of this AD. (2) If cracks are found during any inspections required by this AD that are unacceptable in accordance with the criteria defined in Figures 1 and 2 of the service bulletin, before further flight, either replace cracked parts with new parts of the same part number, after which the aircraft may continue in service for an additional 2,400 hours time in service at which time the inspection requirements of this AD must again be complied with, or comply with paragraph (b) of this AD. (3) If no cracks are found during any inspections required by this AD, reinspect the flap mechanism support structure in accordance with paragraph (a) of this AD at intervals not to exceed 50 landings. (4) If evidence of chafing or less than minimum clearances are found during any inspections required by this AD, rework the area as shown in Figure 3 of the service bulletin or an FAA-approved equivalent, in accordance with the following compliance schedule: (i) Within 10 landings of the inspection where no cracking of structural members is found. (ii) Before further flight, if any cracking is found. (b) Compliance with the provisions of this AD may be terminated upon accomplishment of the modification of the flap mechanism support structure as shown in figure 4 of the service bulletin, or an FAA- approved equivalent. (c) For the purpose of complying with this AD, where airplane landings have not been recorded, number of landings shall be established by assuming two landings for each flight hour recorded. This amendment becomes effective November 28, 1977.
94-25-12: This amendment adopts a new airworthiness directive (AD), applicable to certain Raytheon Corporate Jets Model BAe 125-1000A series airplanes, that requires modification of the galley feeder cables and toilet services fuse. This amendment is prompted by a report that the gauge size of the existing galley feeder cable is not compatible with the rating of the currently used toilet services fuse. The actions specified by this AD are intended to ensure that the subject cables are compatible with the toilet services fuse in order to prevent overheating of the cables, which could result in smoke and fire in the cabin.
2008-10-10 R1: The FAA is revising an existing airworthiness directive (AD), which applies to certain Model 737-600, -700, -700C, -800, and -900 series airplanes. That AD currently requires revising the Airworthiness Limitations (AWLs) section of the Instructions for Continued Airworthiness by incorporating new limitations for fuel tank systems to satisfy Special Federal Aviation Regulation No. 88 requirements. That AD also requires an initial inspection to phase in certain repetitive AWL inspections, and repair if necessary. This AD clarifies the intended effect of the AD on spare and on-airplane fuel tank system components. This AD results from a design review of the fuel tank systems. We are issuing this AD to prevent the potential for ignition sources inside fuel tanks caused by latent failures, alterations, repairs, or maintenance actions, which, in combination with flammable fuel vapors, could result in a fuel tank explosion and consequent loss of the airplane.
2020-26-01: The FAA is superseding Airworthiness Directive (AD) 2019-03- 18, which applied to all Airbus SAS Model A318-111, -112, -121, and - 122 airplanes; Model A319-111, -112, -113, -114, -115, -131, -132, and -133 airplanes; and Model A320-211, -212, -214, -216, -231, -232, and - 233 airplanes. AD 2019-03-18 required repetitive general visual inspections for cracks, and replacement if necessary, of certain main landing gear (MLG) sliding tubes that were subject to improperly performed magnetic particle inspections. This AD continues to require repetitive general visual inspections of the affected MLG sliding tubes for cracks and replacement if necessary, and requires inspections, and replacement if necessary, of additional MLG sliding tubes; as specified in a European Union Aviation Safety Agency (EASA) AD, which is incorporated by reference. This AD was prompted by the identification of additional MLG sliding tubes that might have been subject to the same improperly performed magnetic particle inspection. The FAA is issuing this AD to address the unsafe condition on these products.