Results
2005-11-07: The FAA adopts a new airworthiness directive (AD) for certain Extra Flugzeugproduktions-und Vertriebs-GmbH (EXTRA) Models EA-300, EA- 300S, EA-300L, and EA-300/200 airplanes. This AD requires you to seal with firewall sealant the gaps between the bottom fuselage cover (belly fairing) and the firewall and repeat the sealing procedure whenever you install the bottom fuselage cover (belly fairing). This AD results from mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for Germany. We are issuing this AD to prevent fuel from flowing behind the firewall in the case of a fuel leak. This could result in an in-flight fire, which could cause loss of the airplane and crew.
2005-11-09: The FAA is adopting a new airworthiness directive (AD) for certain Boeing Model 727-200 series airplanes equipped with a No. 3 cargo door. This AD requires repetitive detailed and high frequency eddy current inspections for cracking of the forward, lower corner frame and forward end of the lower beam of the No. 3 cargo door, and corrective actions if necessary. The AD provides an optional terminating action for the repetitive inspections. This AD is prompted by reports of cracking at the forward, lower corner frame and lower beam of the No. 3 cargo door. We are issuing this AD to detect and correct cracking of the forward, lower corner frame and forward end of the lower beam of the No. 3 cargo door, which could result in failure of the affected door stops, loss of the cargo door, and consequent rapid decompression of the airplane.
97-13-01: This amendment adopts a new airworthiness directive (AD), applicable to certain Saab Model SAAB 340B and Model SAAB 2000 series airplanes, that requires a one-time inspection to determine if certain switches are installed on the fire handle of the fire handle assembly; and replacement of the fire handle panel with a new fire handle panel, if necessary. This amendment is prompted by a report indicating that, during manufacture, a batch of defective switches were installed on certain fire handle panels on these airplanes. The actions specified by this AD are intended to ensure the proper switches are installed in the fire handle assembly. A defective switch in the fire handle assembly could prematurely fail and, consequently, prevent the proper operation of the engine fire protection system in the event of a fire.
67-02-01: 67-02-01 BOEING: Amdt. 39-335 Part 39 Federal Register January 4, 1967. Applies to Model 727 Series Airplanes Listed in Boeing Service Bulletin No. 55-15. \n\n\tCompliance required as indicated. \n\n\tCracks have occurred on flanges of the trailing edge hinge fittings of the stabilizer ribs at specific stations and on the stabilizer trailing edge beam. These failures have been attributed to high frequency oscillation of the closing panels and the trailing edge beam. In order to correct this problem, accomplish the following or an equivalent approved by the Chief, Aircraft Engineering Division, FAA Western Region: \n\n\t(a)\tWithin 200 hours' time in service after the effective date of this AD, unless already modified in accordance with (c), and at intervals not to exceed 200 hours' time in service thereafter, comply with either (1) or (2). \n\n\t\t(1)\tUsing eddy current methods inspect for cracks in the stabilizer trailing edge lower beam at Elevator Stations 173.21 and 209.96, in the lower flange of the hinge fitting at Elevator Stations 50.50, 99.79, 136.50, and 173.21 and in the upper flange of the hinge fitting at Elevator Station 50.50 at the fastener locations. \n\n\t\t(2)\tVisually inspect for cracks in the stabilizer trailing edge lower beam at Elevator Stations 173.21 and 209.96, in the lower flange of the hinge fitting at Elevator Stations 50.50, 99.79, 136.50, and 173.21 and in the upper flange of the hinge fitting at Elevator Station 50.50 at the fastener locations. Indication of a crack may be confirmed by a dye penetrant inspection. \n\n\t(b)\tRepair cracked parts before further flight in accordance with a repair approved by the Chief, Aircraft Engineering Division, FAA Western Region. \n\n\t(c)\tWhen an airplane has been modified in accordance with Paragraph II of Service Bulletin 55-7 and Paragraph II of Service Bulletin 55-15, or FAA-approved revisions to these Service Bulletins, the repetitive inspections specified herein may be discontinued. When an airplane has been modified in accordance with Paragraph II of Service Bulletin 55-7 only, or FAA-approved revision to this Service Bulletin, the repetitive inspections specified herein for Elevator Stations 50.50, 99.79, and 136.50 may be discontinued. Immediately prior to accomplishing any modification, inspect in accordance with either (a)(1) or (a)(2) and if cracks are found, repair in accordance with (b). \n\n\tThis supersedes AD 64-17-02. \n\n\tThis directive effective February 3, 1967.
71-08-02: 71-08-02 MCDONNELL DOUGLAS: Amend 39-1189 as amended by amendment 39-1346. Applies to DC-9 airplanes certificated in all categories. \n\n\tCompliance required within the next 50 hours' time in service after effective date of this AD, unless already accomplished. \n\n\tTo ensure pilot control of speed brake retraction and to prevent inflight deployment of ground spoilers, accomplish one of the following: \n\n\t1.\tAffix a placard(s) in the cockpit in plain view of both crew members stating: \n\n\t\tDO NOT EXTEND GEAR WITH SPEED BRAKES DEPLOYED \n\n\t\tDO NOT ARM GROUND SPOILERS PRIOR TO GEAR EXTENSION \n\n\t2.\ta. Install the interlock switch per McDonnell Douglas DC-9 Service Bulletin No. 32-128, dated November 17, 1971, or later FAA approved revisions, or an equivalent modification approved by the Chief, Aircraft Engineering Division, FAA Western Region and \n\n\t\tb.\tAmend the Limitations Section, FAA Approved Airplane Flight Manual, to include the statements: \n\n\t\t\tDo not extend gear withspeed brakes deployed. \n\n\t\t\tDo not arm ground spoilers prior to gear extension. \n\n\tNOTE: Placards previously installed per Step 1. may be removed if step 2 is accomplished. \n\n\tAmendment 39-1189 became effective April 13, 1971. \n\n\tThis amendment 39-1346 becomes effective November 30, 1971.
63-07-03: 63-07-03 PIPER: Amdt. 551 Part 507 Federal Register April 4, 1963. Applies to All Models PA-23 and PA-23-160 Aircraft. Compliance required as indicated. Cracks and loose or working rivets have been found in the attachment area of the rudder trim tab horn, P/N 17059-00, to the rudder trim tab skin, P/N 17068-27. Cracked rudder trim tab ribs P/N 17068-17 also have been found. To preclude the separation of the trim tab horn from the trim tab, accomplish the following: (a) On aircraft having 690 or more hours time in service on the effective date of this AD, within the next 10 hours' time in service unless already accomplished within the last 90 hours' time in service and within each 100 hours' time in service thereafter from the last inspection, accomplish the inspection specified in (c). (b) On aircraft having less than 690 hours' time in service on the effective date of this AD, accomplish the inspection specified in (c) between 600 and 700 hours' time in service and within each 100 hours' time in service thereafter from the last inspection. (c) Visually inspect with at least a 10-power magnifying glass the rudder trim tab horn attach rivets for looseness or evidence of rivet working and the adjacent tab skin for cracks. (d) If skin cracks, loose or working rivets are found, visually inspect the rudder trim tab support rib, P/N 17068-17 for cracks. (e) If any of the defects mentioned herein are found, repair in accordance with Civil Air Regulations Part 18 or replace the affected part, or parts, with an airworthy assembly prior to further flight. (Piper's Periodic Inspection Report pertains to this same subject.) This directive effective April 15, 1963.
2005-11-05: The FAA adopts a new airworthiness directive (AD) for all airplanes equipped with Precise Flight, Inc. (Precise Flight) Models SVS I and SVS IA standby vacuum systems (SVS) installed under certain supplemental type certificates or through field approval. This AD requires you to replace the airplane flight manual supplement (AFMS) in the airplane flight manual with the appropriate revision and install placards as defined in the AFMS, upgrade the Model SVS I or SVS IA SVS to the Model VI SVS, and add the instructions for continued airworthiness (ICA) to the maintenance schedule for the aircraft. This AD results from several reports of failed shuttle control valves of the standby vacuum system (SVS) and one report of an airplane crash with a fatality in which improper use of the SVS was a factor. We are issuing this AD to correct problems with the SVS before failure or malfunction during instrument flight rules (IFR) flight that can lead to pilot disorientation and loss of control of the aircraft.
2005-11-11: The FAA is adopting a new airworthiness directive (AD) for certain Bombardier Model DHC-8-400, -401, and -402 series airplanes. This AD requires repetitive inspections to detect discrepancies of the attachment fittings of the outboard flap front spar at flap track Number 4 and Number 5 locations, and corrective actions if necessary. This AD also requires eventual replacement of the attachment fittings as terminating action for the repetitive inspections. This AD is prompted by the discovery of several airplanes that have loose flap front spar attachment fittings at flap track Number 4 and Number 5 locations. We are issuing this AD to prevent the attachment fittings from becoming detached, and consequent loss of control of the airplane.
71-17-08: 71-17-08 CESSNA: Amdt. 39-1273. Applies to Model 337 Airplanes. Compliance. To minimize the possible adverse affects of undetected rear engine stoppage during take-off, within the next 10 hours' time in service after the effective date of this AD, the following modifications must be accomplished and the following operational procedures will be applicable: A) Readjust the rear engine idle RPM from 575-625 to 625-675 and readjust idle mixture accordingly. B) Taxi primarily by use of the rear engine. C) Initiate all take-offs by advancing the throttle on the rear engine to a point where the normal functioning of the rear engine has been established before advancing the throttle of the front engine. D) Install a permanent placard to the right of the tachometer instrument to read as follows: TAXI AND TAKE-OFF LEAD WITH REAR ENGINE POWER CHECK RPM AND FUEL FLOW NOTE: The operator may make and install a temporary placard using minimum 1/8 inch highletters until the permanent placard is obtained from the manufacturer and properly installed. Cessna Service Letter ME 71-21 refers to the subject matter of this AD. This amendment becomes effective August 24, 1971.
62-26-06: 62-26-06 PIPER: Amdt. 516 Part 507 Federal Register December 8, 1962. Applies to All Models PA-28-150 and PA-28-160 Airplanes With Serial Numbers 28-03, 28-1 through 28-671, 28-678, 28-679, 28-681, 28-685, 28-690, 28-691, 28-693, 28-697, 28-706, and 28-707, Except Those With Exhaust Assembly P/N 63726 Installed. Compliance required within the next 10 hours' time in service after the effective date of this AD, and each 50 hours' time in service thereafter. There have been cracks found in the exhaust system on Piper PA-28-150 and PA-28-160 airplanes. As this condition is likely to occur in other airplanes of the same type design, accomplish the following: (a) Remove carburetor heat muff shroud and conduct a close visual inspection of the complete exhaust system piping for cracks in all welded joints and tubing bends. Pay particular attention to the area near the junction of the cylinder stacks and main exhaust manifold. (b) If cracks are found, repair by gaswelding. (The exhaust pipe is AISI 321 or 347 corrosion resistant steel.) (Piper Service Letter 389 covers this same subject.) This directive effective December 14, 1962.