Results
2018-07-01: We are superseding Airworthiness Directive (AD) 2013-16-14 for Eurocopter Deutschland GmbH (now Airbus Helicopters Deutschland GmbH) Model EC 135 P1, P2, P2+, T1, T2, and T2+ helicopters. AD 2013-16-14 required installing a washer in and modifying the main transmission filter housing upper part. Since we issued AD 2013-16-14, Airbus Helicopters Deutschland GmbH has extended the overhaul interval for the main transmission and determined that other models may have the same unsafe condition. This AD retains the requirements of AD 2013-16-14, adds models to the applicability, and revises [[Page 13381]] the required compliance time for the modification. The actions of this AD are intended to correct an unsafe condition on these products.
2001-05-01: This amendment adopts a new airworthiness directive (AD) that applies to certain DG Flugzeugbau GmbH (DG Flugzeugbau) Model DG-500MB sailplanes equipped with a SOLO 2625 02 engine. This AD requires you to install additional access holes in the propeller mount and modify the engine. This AD also requires you to do a ground test run and replace the digital engine indicator circuit breaker. This AD is the result of mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for the Federal Republic of Germany. The actions specified by this AD are intended to correct an inadequate circuit breaker and unsatisfactory drive belt tension that could cause damage to the engine crankshaft. Such damage could lead to engine failure and loss of control of the sailplane.
2018-06-11: We are adopting a new airworthiness directive (AD) for certain Textron Aviation Inc. Models A36TC, B36TC, S35, V35, V35A, and V35B airplanes. This AD was prompted by a fatal accident where the exhaust tailpipe fell off during takeoff. This AD adds a life limit to the exhaust tailpipe v-band coupling (clamp) that attaches the exhaust tailpipe to the turbocharger and requires an annual visual inspection of the exhaust tailpipe v-band coupling (clamp). We are issuing this AD to address the unsafe condition on these products.
78-23-04: 78-23-04 PIPER: Amendment 39-3340. Applies to Piper Model PA-38-112 Serial Nos. 38-78A0001, 38-78A0005 thru 38-78A0016, 38-78A0018 thru 38-78A0039, 38-78A0042 thru 38-78A0130, 38-78A0132 thru 38-78A0212, 38-78A0214 thru 38-78A0233, 38-78A0235 thru 38-78A0270, 38-78A0272 thru 38-78A0324, 38-78A0326 thru 38-78A0329, 38-78A0331, 38-78A0333 thru 38-78A0356, 38-78A0358 thru 38-78A0372, 38-78A0374, 38-78A0375, 38-78A0377 thru 38-78A0385, 38-78A0387 thru 38-78A0399, 38-78A0401 thru 38-78A0410, 38-78A0413, 38-78A0415, 38-78A0416, 38-78A0418 thru 38-78A0421, 38-78A0424 thru 38-78A0426, 38-78A0428, 38-78A0429, 38-78A0431, 38-78A0432, 38-78A0434, 38-78A0435, 38-78A0437 thru 38-78A0439, 38-78A0441 thru 38-78A0443, 38-78A0445, 38-78A0446, 38-78A0449 thru 38-78A0455, 38-78A0457 thru 38-78A0466, 38-78A0468, 38-78A0469, 38-78A0471, 38-78A0472, 38-78A0474, 38-78A0475, 38-78A0477, 38-78A0478, 38-78A0480, 38-78A0481, 38-78A0483, 38-78A0484, 38-78A0486, 38-78A0489, 38-78A0490, 38-78A0492 thru 38-78A0494, 38-78A0496 thru 38-78A0498, 38-78A0500 thru 38-78A0502, 38-78A0504 thru 38-78A0506, 38-78A0509, 38-78A0510, 38-78A0512 thru 38-78A0526, 38-78A0528 thru 38-78A0532, 38-78A0534, 38-78A0535, 38-78A0537, 38-78A0538, 38-78A0540, 38-78A0541, 38-78A0544, 38-78A0546 thru 38-78A0548, 38-78A0550, 38-78A0552, 38-78A0555, 38-78A0556, 38-78A0558, 38-78A0559, 38-78A0561, 38-78A0565, 38-78A0567, 38-78A0568, 38-78A0570, 38-78A0573, 38-78A0574, 38-78A0576, 38-78A0578, 38-78A0581, 38-78A0584, 38-78A0585, 38-78A0587, 38-78A0588, 38-78A0606 and 38-78A0622. To prevent weakening of the wing rear spar to fuselage attach fitting connection due to missing rivets, accomplish the following: (a) Within the next 10 hours in service after the effective date of this AD, unless already accomplished, perform the steps 1 thru 4 as indicated under the Instructions section in Piper Service Bulletin No. 618, dated September 5, 1978, or equivalent. (b) Equivalent inspections, repairs, and alterations must be approved by the Chief, Engineering and Manufacturing Branch, FAA, Eastern Region. (c) The affected airplanes may be flown in accordance with FAR 21.197 to a location where the AD may be accomplished. (d) Upon submission of substantiating data through an FAA Maintenance Inspector, the compliance time specified in this AD may be adjusted by the Chief, Engineering and Manufacturing Branch, FAA, Eastern Region. This amendment is effective November 10, 1978.
2007-16-05: The FAA is adopting a new airworthiness directive (AD) for all Boeing Model 737-100, -200, -200C, -300, -400, and -500 series airplanes. This AD requires repetitive inspections for discrepancies of the elevator tab control rod assemblies and/or damage to the surrounding structure, and related corrective action. This AD results from reports indicating loose jam nuts and/or thread wear at the rod ends on the elevator tab control rod assembly. We are issuing this AD to find and fix discrepancies of the elevator tab control rod assembly, which could result in excessive freeplay in the elevator tab control rods. Such freeplay could cause loss of both load paths, subsequent elevator tab flutter, and consequent reduced structural integrity and loss of controllability of the airplane.
2001-05-05: This amendment adopts a new airworthiness directive (AD) that is applicable to certain Boeing Model 747 series airplanes. This action requires repetitive detailed visual inspections to find discrepancies of the installation of the midspar fuse pins of the inboard and outboard struts, and follow-on actions, if necessary. This action also provides for an optional terminating modification for the repetitive inspections. This action is necessary to find and fix discrepancies of the installation of the midspar fuse pins, which could result in loss of the secondary retention capability of the fuse pins, migration of the fuse pins, and consequent loss of the strut and engine from the airplane. This action is intended to address the identified unsafe condition.
2019-17-05: The FAA is adopting a new airworthiness directive (AD) for certain Airbus SAS Model A330-200 Freighter, -200, and -300 series airplanes; and certain Airbus SAS Model A340-200, -300, -500, and -600 series airplanes. This AD was prompted by a determination that certain wing slat tracks that were inadvertently indicated as eligible for installation on all Model A330 and A340 series airplanes are unable to sustain the ultimate loads relative to the weight variant of certain airplane configurations. This AD requires identifying affected parts, inspecting for and repairing cracks, and replacing affected parts with serviceable parts, as specified in a European Aviation Safety Agency (EASA) AD, which is incorporated by reference. The FAA is issuing this AD to address the unsafe condition on these products.
78-22-07: 78-22-07 PIPER AIRCRAFT CORPORATION: Amendment 39-3332. Applies to the following model PA-32RT-300 and PA-32RT-300T aircraft, certificated in all categories: PA-32RT-300 Lance II 32R-7885001 to 32R-7885216 Inclusive 32R-7885218 to 32R-7885253 Inclusive 32R-7885255, 32R-7885257 to 32R-7885260 Inclusive PA-32RT-300T Turbo Lance II 32R-7887001 to 32R-7887110 Inclusive 32R-7887112 to 32R-7887173 Inclusive 32R-7887175 to 32R-7887182 Inclusive 32R-7887184 to 32R-7887196 Inclusive 32R-7887198 to 32R-7887201 Inclusive 32R-7887203 to 32R-7887205 Inclusive 32R-7887207, 32R-7887208, 32R-7887210, 32R-7887212 to 32R-7887215 Inclusive 32R-7887217, 32R-7887218, 32R-7887220, 32R-7887222, 32R-7887224 and 32R-7887226. Compliance required within the next 10 hours of operation, or at the next regularly scheduled or annual inspection, whichever occurs first. To insure full travel of the control column, replace the control column stop sleeve and checkcontrol column travel and stabilator travel in accordance with the instructions contained in Piper Service Bulletin 619 (and Control Column Stop Modification Kit Number 763 895V) or later revision approved by the Chief, Engineering and Manufacturing Branch, Federal Aviation Administration, Southern Region, or in an equivalent manner approved by the Chief, Engineering and Manufacturing Branch, Federal Aviation Administration, Southern Region. This amendment becomes effective November 15, 1978.
2007-16-11: The FAA is adopting a new airworthiness directive (AD) for certain Fokker Model F27 Mark 050 airplanes equipped with Dowty Type R.352 or R.410 series propellers. This AD requires checking the maintenance records to determine whether Minnesota Mining and Manufacture Co. (3M) 1300L adhesive was used to attach the de-icer assembly overshoes (boots) to the propeller blades, repetitive inspections of affected boots, and replacing boots attached with defective adhesive. This AD results from three events of propeller blade de-icer assembly boots debonding and detaching during flight. This condition was caused by using 3M 1300L adhesive to attach the boot to the propeller blade. We are issuing this AD to detect and correct boots attached with defective adhesive, which could result in debonding and separation of a boot from the airplane, consequent reduced structural integrity of the airplane, and possible injury to passengers and crew.
2019-17-03: The FAA is adopting a new airworthiness directive (AD) for certain Airbus SAS Model A320-214 and -271N airplanes and Model A321- 211 and -231 airplanes. This AD was prompted by a test of a new wall partition for a certain cabin attendant seat model that revealed the backrest was permanently deformed and did not allow the seat pan to return to a full-up position; investigation results identified that a heat treatment had not been applied on certain backframes. This AD requires modifying the affected cabin attendant seats, as specified in a European Aviation Safety Agency (EASA) AD, which is incorporated by reference. The FAA is issuing this AD to address the unsafe condition on these products.