Results
2013-07-08: We are adopting a new airworthiness directive (AD) for certain The Boeing Company Model 757 airplanes. This AD was prompted by reports that inspections of the wing center section revealed defective, misapplied, or missing secondary fuel vapor barriers on the center fuel tank. This AD requires inspecting for discrepancies and insufficient coverage of the secondary fuel barrier, determining the thickness of the secondary fuel barrier, and corrective actions if necessary. We are issuing this AD to detect and correct defective surfaces and insufficient thickness of the secondary fuel barrier, which could allow fuel leaks or fumes into the pressurized cabin, and allow fuel or fuel vapors to come in contact with an ignition source, which could result in a fire or an explosion.
75-16-11: 75-16-11 PILATUS AIRCRAFT LTD: Amdt. 39-2284. Applies to B4-PC11 gliders, serial numbers 141 and subsequent, certificated in all categories. Compliance is required as indicated. To prevent rudder cable chaffing, jamming, or separation accomplish the following: (a) Within 10 hours' time in service after the effective date of this AD, unless already accomplished, visually inspect the rudder control cables for chaffing in that portion adjacent to the crotch strap attachment brackets and repair, or replace as required in accordance with the Pilatus B4- PC11 Maintenance Manual or an FAA-approved equivalent. (b) Within 25 hours' time in service after the effective date of this AD, unless already accomplished, install a polyurethane foam block P/N 112.50.11.065 on the underside of the pilot seat to provide a grooved channel to cover the crotch strap attachment bracket in accordance with the accomplishment instructions set forth in Pilatus Aircraft Service Bulletin No. 1002 datedMay 1974, or an FAA-approved equivalent. This amendment becomes effective July 29, 1975.
2013-04-04: We are superseding an existing airworthiness directive (AD) for certain The Boeing Company Model 757 airplanes equipped with Rolls- Royce RB211-535E engines. That AD currently requires repetitive inspections for signs of damage of the aft hinge fittings and attachment bolts of the thrust reversers, and related investigative and corrective actions if necessary. The existing AD also provides for an optional terminating modification for the repetitive inspections. For certain airplanes, this new AD adds a one-time inspection of the washers installed under the attachment bolts of the aft hinge fittings for correct installation sequence, and reinstallation if necessary. This new AD also adds an option for installing a redesigned aft hinge fitting with the trim already done, instead of trimming an existing or new hinge fitting, which is included in the existing optional terminating modification. This AD was prompted by reports of incorrectly installed washers under the attachment bolts of the aft hinge fittings of the thrust reversers. We are issuing this AD to prevent failure of the attachment bolts and consequent separation of a thrust reverser from the airplane during flight, which could result in structural damage to the airplane.
2013-07-02: We are adopting a new airworthiness directive (AD) for all Airbus Model A318, A319, and A320 series airplanes. This AD was prompted by fuel system reviews conducted by the manufacturer, which revealed that certain fuel pumps under certain conditions can create an ignition source in the fuel tank. This AD requires modification of the center tank fuel pump control circuit by installation of ground fault interrupters (GFIs). This AD would also require either replacement of the GFI or deactivation of the associated fuel pump following failure of any post-modification operational test of the GFI. We are issuing this AD to prevent the potential of ignition sources inside fuel tanks, which, in combination with flammable fuel vapors, could result in fuel tank explosions and consequent loss of the airplane.
2025-05-14: The FAA is adopting a new airworthiness directive (AD) for all Airbus SAS Model A350-941 and A350-1041 airplanes. This AD was prompted by a report indicating that the thrust reverser and pylon thermal blankets were found damaged due to air leaking from the pre-cooler exchanger (PCE). This AD requires repetitively testing the PCE for air leaks and reporting the results, and, depending on findings, inspecting the thermal blankets for damage and replacing the PCE, as specified in a European Union Aviation Safety Agency (EASA) AD, which is incorporated by reference. The FAA is issuing this AD to address the unsafe condition on these products.
2013-06-07: We are adopting a new airworthiness directive (AD) for Eurocopter France (Eurocopter) Model SA-365N1, AS-365N2, and AS 365 N3 [[Page 20235]] helicopters. This AD requires revising the Limitations section of the Rotorcraft Flight Manual (RFM) to prohibit flight in instrument meteorological conditions (IMC) or night visual flight rules (VFR) for each helicopter with a vertical gyro unit GV76-1 installed upon a non- reinforced shelf in the rear cargo compartment. Also, this AD requires modifying the GV76-1 vertical gyro unit shelf and testing for correct function of the navigation systems. This AD was prompted by flight crew reports of deviations between the displayed attitude on the attitude display screen and the independent electromechanical standby attitude indicator. The actions of this AD are intended to prevent an undetected flight display error of a slow drift in the roll axis, disorientation of the pilot, and subsequent loss of control of the helicopter.
2013-06-05: We are superseding an existing airworthiness directive (AD) for all The Boeing Company Model 737-600, -700, -700C, -800, -900, and -900ER series airplanes. That AD currently requires repetitive inspections of the aft attach lugs of the elevator tab control mechanisms, and replacement of any discrepant elevator tab control mechanism. This new AD requires replacing the left and right elevator tab control mechanisms with elevator tab control mechanisms that have the modified attach lugs, which would terminate the existing requirements. This AD was prompted by reports of failure of the aft attach lugs on the elevator tab control mechanisms, which resulted in severe elevator vibration; and reports of gaps in elevator tab control mechanisms and analysis indicating that additional elevator tab control mechanisms might have bearings that will come loose. We are issuing this AD to prevent discrepancies in the aft attach lugs of the elevator tab control mechanism, which could result insevere elevator and tab vibration. Consequent structural failure of the elevator or horizontal stabilizer could result in loss of structural integrity and aircraft control.
74-22-01: 74-22-01 MCDONNELL DOUGLAS: Amendment 39-1995, as amended by amendment 39-3487. Applies to all Model DC-9 -10, -20, -30, -40 and military C-9A and C-9B Series airplanes equipped with welded aft engine isolator mount(s), P/N K2219-6SA3, certificated in all categories. \n\n\tTo detect cracks in the welded aft engine mounts, accomplish the following: \n\n\tFor airplanes equipped with welded aft engine isolator mount(s) with more than 4,000 hours time-in-service on the effective date of this AD, within the next 300 hours time-in-service, unless previously accomplished within the last 450 hours time-in-service, and thereafter at intervals not to exceed 850 hours time-in-service, inspect the aft engine mount per McDonnell Douglas All Operators' Letter AOL 9-786, dated December 13, 1973, AOL 9-786A dated March 27, 1974, AOL 9-786B dated April 8, 1974, or an equivalent approved by the Chief, Aircraft Engineering Division, FAA Western Region. If any cracks are detected replace the part before further flight with a forged part, P/N's K2219-6SA5 and K2219-7SA3, or an uncracked welded part K2219-6SA3. Upon installation of a forged part the requirements of this A.D. are terminated. \n\n\tNOTE: (A) For the purposes of this A.D. if the time-in-service hours of the aft engine isolator mount cannot be established the part will be considered to have the same number of time-in-service hours as the airplane on which it is installed. \n\n\t\t(B)\tThe airplane may be flown in accordance with FAR's 21.197 21.199 to a base where the inspection can be performed. \n\n\tAmendment 39-1995 became effective November 25, 1974. \n\n\tThis amendment 39-3487 becomes effective June 12, 1979.
2013-05-10: We are adopting a new airworthiness directive (AD) for certain The Boeing Company Model 777 airplanes. This AD was prompted by reports that escape slides/rafts did not deploy due to galvanic corrosion of the door-mounted slide/raft packboard release mechanisms. This AD requires doing a general visual inspection of the housing assembly of the packboard release mechanism to determine if its surface treatment has been sealed, and if the surface of the housing assembly is unsealed, replacing the housing assembly with a new or serviceable housing assembly. We are issuing this AD to detect and correct corrosion of the packboard release mechanisms, which could interfere with escape slide/raft deployment, prohibit doors from opening in the armed mode, and cause consequent delay and injury during evacuation of passengers and crew from the cabin in the event of an emergency.
2013-06-03: We are adopting a new airworthiness directive (AD) for all Airbus Model A318, A319, A320, and A321 series airplanes. This AD was prompted by reports of oil residue between the stator and the rotor parts of the position resolvers of the angle of attack (AOA) vane, which was a result of incorrect removal of the machining oil during the manufacturing process of the AOA resolvers. This AD requires an inspection to determine if certain AOA probes are installed, and replacement of any affected AOA probe. We are issuing this AD to prevent erroneous AOA information and consequent delayed or non- activation of the AOA protection systems, which during flight at a high AOA, could result in reduced control of the airplane.
2019-05-02: We are superseding airworthiness directive (AD) 2017-22-13 for certain Rolls-Royce plc (RR) RB211-Trent 900 turbofan engine models. AD 2017-22-13 required an inspection of the drains mast and the replacement or repair of the drains mast if a crack is found. This AD retains this requirement, but adds repetitive inspections and expands the population of affected RR RB211-Trent 900 turbofan engine models. This AD was prompted by RR in-service findings that indicated a need to include part number (P/N) FW29847 drains mast and additional RR RB211- Trent 900 turbofan engines to the affected population. We are issuing this AD to address the unsafe condition on these products.
2013-05-12: We are adopting a new airworthiness directive (AD) for certain Embraer S.A. Model ERJ 170 and ERJ 190 airplanes. This AD was prompted by a report that high rate discharge (HRD) bottle explosive cartridges of a cargo compartment fire extinguisher system were swapped between the forward and aft cargo compartments. Additional investigation also revealed the possibility of swapping between the electrical connectors of the HRD and low rate discharge (LRD) bottles, and a rotated installation of the HRD bottle. Improper assembly of the fire extinguishing bottle might cause the extinguishing agent to be discharged toward the unselected cargo compartment rather than toward the cargo compartment with fire. This AD requires an inspection of the HRD bottle for correct installation and to determine if the pressure switch is in the correct position, and re-installation if necessary; an inspection of the HRD and LRD bottle discharge heads to determine the part number, and replacement if necessary; and, for certain airplanes, an inspection to identify the HRD and LRD bottle electrical connectors, and relocation if necessary. We are issuing this AD to prevent the inability of the fire extinguishing system to suppress fire.
85-07-09: 85-07-09 AIRBUS INDUSTRIE: Amendment 39-5033. Applies to Model A300 B2 and B4 series airplanes, manufacturer serial numbers 003 through 156, certificated in all categories. To prevent rapid decompression of the aircraft, accomplish the following, unless already accomplished. Compliance is required within the time schedules indicated below, or within six months after the effective date of this AD, whichever occurs later: A. Prior to the threshold limits specified in Table 1 of Airbus Industrie Service Bulletin A300-53-148, Revision 6, dated October 10, 1984, inspect the fuselage longitudinal lap joints and circumferential joints for bonding delamination in accordance with the accomplishment instructions of the service bulletin: 1. If no delamination is detected, repeat these inspections in accordance with the schedule shown in Table 1 of the service bulletin. 2. If delamination is detected in any of the inspections above, perform the actions indicated in Figure 3,Follow-up Action, of the service bulletin. B. Prior to the threshold limits specified in Figure 1, Inspection Program, of Airbus Industrie Service Bulletin A300-53-178, Revision 4, dated October 10, 1984, visually inspect for corrosion and cracks, and repair if necessary, the bonded longitudinal lap joints and circumferential joints specified in Figure 1 of the service bulletin, in accordance with the accomplishment instructions of the service bulletin. Repeat the inspections in accordance with the schedule shown in Figure 1 of the service bulletin. C. Prior to the threshold limits specified in Figure 1, Inspection Frequency, of Airbus Industrie Service Bulletin A300-53-149, Revision 6, dated October 10, 1984, inspect for debonding and repair, if necessary, bonded stringers and bonded doublers in the area between frame 1 and frame 18 and between frame 40 and frame 80 on all airplanes up to and including serial number 156, and in the area between frame 18 and frame 40 on all airplanes up to and including serial number 104, in accordance with the accomplishment instructions of the service bulletin. The inspections of stringers is divided into three areas, as indicated in Figure 2 of the service bulletin with the following options: (1) Inspection in Area 1 is not required if Modification No. 2904, described in Airbus Industrie Service Bulletin A300-53-146, dated November 28, 1980, has been incorporated. (2) Preventive riveting of stringers located in Area 2 in accordance with Airbus Industrie Service Bulletin A300-53-197, dated October 10, 1984, allows for an extension of the interval of subsequent repetitive inspections to the interval required for Area 3. D. 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. 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 and/or modifications required by this AD. This amendment becomes effective May 13, 1985.
76-05-03: 76-05-03 UNITED AIRCRAFT OF CANADA LIMITED: Amendment 39-2535. Auxiliary Power Unit Model ST6L-73. Compliance required as indicated unless previously accomplished. To preclude leakage of the Sundstrand Aviation 025277 series fuel pump without the part number 5002557 injector cap and screen assembly, accomplish the following: (a) Within the next twenty hours in service after the effective date of this AD, unless previously accomplished, inspect all fuel pumps with less than 250 hours time in service since new in accordance with paragraph 2, Accomplishment Instructions of Pratt & Whitney of Canada Limited Alert Service Bulletin No. 9046 dated August 19, 1975, or approved equivalent inspection. (b) Within the next 250 hours in service after the effective date of this AD, unless previously accomplished, install part number 5002557, injector cap and screen assembly, in accordance with paragraph 2, Accomplishment Instructions of Pratt & Whitney Aircraft of Canada Limited Service Bulletin No. 9043, dated September 2, 1975, or approved equivalent instructions. The aircraft may be flown in accordance with FAR 21.197 to a base where the alteration or inspection can be performed. An equivalent alteration or inspection must be approved by the Chief, Engineering and Manufacturing Branch, of the Eastern Region of the FAA. This amendment is effective March 9, 1976.
75-19-02: 75-19-02 LOCKHEED: Amendment 39-2362 as amended by Amendment 39-2513 and Amendment 39-2625 is further amended by Amendment 39-3158. Applies to all model 382 series airplanes, serial numbers 3946 and 4101 through 4541. On airplane serial numbers 3946 and 4101 through 4298 with 6,300 hours or more total time in service, and on airplane serial numbers 4299 through 4541 with 9,450 hours or more total time in service on the effective date of Amendment 39-3158 unless already accomplished, eddy current inspect the outer wing lower aft beam caps at OWS 54 and 108 in accordance with Hercules Airfreighter Inspection Procedures SMP 515-A Card No. SP-88, revised August 11, 1975. Reinspect at intervals not to exceed 3400 hours time in service from the last inspection until 20,000 hours, (without ECP 954) or 24,000 hours, (with ECP 954) at which time the interval is not to exceed 1700 hours time in service from the last inspection. If a crack or cracks are found, before further flight, contactthe Chief, Engineering and Manufacturing Branch, FAA, Southern Region, Atlanta, Georgia, telephone number 404-526-7428. Before the accumulation of more than 30,000 flight hours, preventive modification shall be installed in accordance with Lockheed Service Bulletin 382-187, or later FAA-Approved revision, or in an equivalent manner approved by the Chief, Engineering and Manufacturing Branch, FAA, Southern Region. The inspections required by this AD may be discontinued for those airplanes which have been modified in accordance with the above paragraph. Amendment 39-2362 superseded Amendment 39-2249, FR Doc. 75-17068, AD 75-14-05. Amendment 39-2362 was effective September 12, 1975, and was effective June 13, 1975, for all recipients of the telegrams dated June 13, 1975, and August 25, 1975, which contained this amendment. Amendment 39-2513 became effective February 13, 1976. Amendment 39-2625 became effective June 4, 1976. This amendment 39-3158 becomes effective March 20, 1978.
2018-04-09: We are adopting a new airworthiness directive (AD) for Pacific Aerospace Limited Model 750XL airplanes. This AD results from mandatory continuing airworthiness information (MCAI) issued by an aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as incorrectly marked and annunciated low oil pressure indication warnings. We are issuing this AD to require actions to address the unsafe condition on these products.
2013-06-04: 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 an aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as fretting (wear and/or chafing) found between the elevator pushrod assembly and the horizontal tail structure, which could cause the elevator pushrod to jam and could result in loss of control. We are issuing this AD to require actions to address the unsafe condition on these products.
2003-10-05: This amendment adopts a new airworthiness directive (AD) that applies to certain Raytheon Aircraft Company (Raytheon) Model 390 airplanes. This AD requires you to incorporate information into the FAA-approved Airplane Flight Manual (AFM) that would add requirements for "Landing Performance for Operation of the Airplane with Lift Dump Inoperative." This AD is the result of two accidents on the affected airplanes where a contributing factor was the lift dump spoilers failing to deploy when commanded after the initial landing. The FAA previously issued AD 2003-07-09 affecting certain Model 390 airplanes. However, the airplane serial numbers included in this AD were inadvertently omitted from AD 2003-07-09. The actions specified by this AD are intended to require the use of necessary flight information to prevent runway overruns based on insufficient wheel braking if the lift dump spoilers do not operate after landing touchdown. This could result in reduced or loss of control of the airplane. DATES: This AD becomes effective on May 30, 2003. The Director of the Federal Register previously approved the incorporation by reference of certain publications listed in the regulation as of April 7, 2003 (68 FR 16205, April 3, 2003). The Federal Aviation Administration (FAA) must receive any comments on this rule on or before July 2, 2003.
47-49-08: 47-49-08 LOCKHEED: (Was Service Note 8 of AD-763-3.) Applies to All Model 49 Serials Up to and Including 2046. At periods not to exceed 250 hours, inspect the aileron leading edge ribs at Stations 571 and 577, the adjacent leading edge skin and the counterbalance supports for signs of cracks. When cracks are found, install heavier supports, new rib elements, new leading edge skin, and rib reinforcements, as required. When both ribs have been reinforced and heavier supports installed, this periodic inspection may be discontinued. (LAC Service Bulletin 49/SB-162 covers this same subject.)
96-21-12 PL: 96-21-12 BELL HELICOPTER TEXTRON, A DIVISION OF TEXTRON CANADA LTD.: Priority Letter issued on October 11, 1996. Docket No. 96-SW-34-AD. Applicability: Model 407 helicopters, 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 (d) 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 immediately upon receipt of this AD. To prevent uncommanded inflight engine shut-downs, accomplish the following: (a) Do not fly the helicopter. (b) Manufacture a placard that states "Flight Of This Helicopter Is Prohibited". The placard shall be manufactured of a material that cannot be easily defaced or erased, and the lettering shall be block-style and at least 2-inches high but not more than 6-inches high. Additionally, the color of the lettering must contrast with the background (color of the placard material) so that it is legible. Install the placard in the pilot-side window of the helicopter. Do not remove the placard from the helicopter until corrective action(s) have been issued by the FAA in the form of an AD, and have been accomplished. (c) Insert a copy of this AD into each BHTC Model 407 helicopter maintenance records. (d) 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, Rotorcraft Certification Office, Rotorcraft Directorate, FAA. Operators shall submit their requests through an FAA Principal Maintenance Inspector, who may concur or comment and then send it to the Manager, Rotorcraft Certification Office. NOTE 2: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Rotorcraft Certification Office. (e) Special flight permits will not be issued. Flight testing of a helicopter affected by this AD, by Bell Helicopter Textron, Inc. only, may be permitted if approved by the Manager, Rotorcraft Certification Office, Rotorcraft Directorate, FAA. (f) Priority Letter AD 96-21-12, issued October 11, 1996, becomes effective upon receipt.
2018-02-17: We are superseding Airworthiness Directive (AD) 2012-12-12 and AD 2013-16-26, which applied to all Airbus Model A330-200, A330-200 Freighter, A330-300, A340-200, and A340-300 series airplanes. AD 2012- 12-12 required repetitive inspections of the outer skin rivets of the cargo doors, repair if necessary, and other repetitive inspections. AD 2013-16-26 required repetitive inspections of certain cargo doors, and repair if necessary. This new AD continues to require repetitive inspections, and repair if necessary. This new AD revises the applicability; adds a one-time inspection and adjustment of certain hook gaps; reinforcement of the door frame structure; related investigative and corrective actions if necessary; and a modification, which allows deferring reinforcement of the cargo door structure. This AD was prompted by a determination that a new inspection procedure is necessary to address the unsafe condition. We are issuing this AD to address the unsafe condition on these products.
2013-03-10: We are adopting a new airworthiness directive (AD) for certain Lindstrand Hot Air Balloons Ltd female ACME threaded hose connectors, part numbers HS6139 and HS6144, installed on balloons. This AD results from mandatory continuing airworthiness information (MCAI) issued by an aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as insufficient tightness of the threaded hose connector in the assembly area that could result in fuel leakage. We are issuing this AD to require actions to address the unsafe condition on these products.
2003-10-02: The FAA is adopting a new airworthiness directive (AD) for Rolls-Royce plc (RR) RB211-524C2-19 and RB211-524C2-B-19 series turbofan engines. This AD requires replacing the existing low pressure (LP) compressor location bearing assembly, intermediate pressure (IP) compressor location bearing, IP compressor bearing support housing, IP compressor rear stub shaft, LP compressor location bearing support, oil transfer connector assembly, hydraulic oil seal housing, and hydraulic oil seal with improved design parts. This AD is prompted by statistical analysis by the manufacturer of in-service premature bearing failures. The actions specified in this AD are intended to prevent LP compressor failure and uncontained disc failures, resulting in damage to the airplane.
84-19-08: 84-19-08 HILLER HELICOPTERS, a subsidiary of Rogerson Aircraft Corp (formerly Hiller Aviation): Amendment 39-4914. Applies to Model UH-12D and UH-12E series helicopters equipped with engine mount Part No. 63181-5 certificated in any category which have been converted to turbine power by STC SH177WE or SH178WE. Compliance is required as indicated (unless already accomplished). (a) Within the next 20 hours time in service after the effective date of this AD, and thereafter at intervals not to exceed 600 hours time in service from the last inspection, remove the paint from the outer gimbal forward attach fitting of the Hiller engine mount Part No. 63181-5 and dye penetrant or magnetic particle inspect the gusset weld beads for cracks on both the front and back sides of the gusset. (b) If cracks are found, replace the engine mount Part No. 63181-5 before further flight. (c) Prior to or immediately following installation or reinstallation of engine mount Part No.63181-5 in any of the Model UH-12 series helicopters listed above, perform the inspection required by paragraph (a) of this AD. (d) Alternative inspections, modifications, or other actions which provide an equivalent level of safety may be used when approved by the Manager, Seattle Aircraft Certification Office, FAA, 17900 Pacific Highway South, C-68966, Seattle, Washington 98168. This supersedes Amendment 39-3538 (44 FR 50035; August 27, 1979), AD 79-18-01. This amendment becomes effective September 20, 1984.
2018-04-10: We are adopting a new airworthiness directive (AD) for Pilatus Aircraft Limited Model PC-7 airplanes. This AD results from mandatory continuing airworthiness information (MCAI) issued by an aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as the brakes remaining activated after release of the brake pedal. We are issuing this AD to require actions to address the unsafe condition on these products.