Results
2005-25-24: The FAA is adopting a new airworthiness directive (AD) for certain Boeing Model 777-200 and -300 series airplanes. This AD requires repetitive detailed inspections of the forward lugs of the power control unit (PCU), yoke assembly, and forward attachment hardware of the left inboard, left outboard, right inboard, and right outboard flaperon PCUs; and other specified/corrective actions if necessary. For certain airplanes, this AD also requires other related concurrent actions. This AD results from reports indicating that operators have found worn, fretted, and fractured bolts that attach the yoke assembly to the flaperon PCU. We are issuing this AD to prevent damage and eventual fracture of the yoke assembly, pin assembly, and attachment bolts that connect the inboard and outboard PCUs to a flaperon, which could lead to the flaperon becoming unrestrained and consequently departing from the airplane. Loss of a flaperon could result in asymmetric lift and reduced roll control ofan airplane. A departing flaperon could also cause damage to the horizontal and vertical stabilizers, which could result in loss of control of the airplane if damage is significant.
98-26-11: This amendment adopts a new airworthiness directive (AD), applicable to certain Saab Model SAAB 2000 series airplanes, that requires replacement of the end-pieces of the expansion chamber attenuator (ECA) for the standby pump of the Number 2 hydraulic system with new, improved end-pieces. This amendment is prompted by issuance of mandatory continuing airworthiness information by a foreign civil airworthiness authority. The actions specified by this AD are intended to prevent leakage of hydraulic fluid from the Number 2 hydraulic system due to failure of the end-pieces of the ECA, which could result in loss of nose wheel steering, flap operation, normal landing gear operation, and reduced redundancy in the brake and flight controls systems.
80-02-17: 80-02-17 CESSNA: Amendment 39-3675. Applies to Model 441 (S/Ns 441-0001 thru 441-0106 and 441-0109 airplanes). COMPLIANCE: Required as indicated unless already accomplished. To preclude accidents resulting from the inability of the airplane to meet flight manual performance data, prior to further flight accomplish either paragraph A) or B) below: A) Install Revision 5 dated March 26, 1979, in the Pilot's Operating Handbook and FAA Approved Airplane Flight Manual and operate the airplane in accordance with this revision. (This action was required by AD 79-10-08 on S/Ns 441-0001 through 441-0097 airplanes and incorporated in Airplanes S/Ns 441-0098 through 441-0106 and S/N 441-0109 by the manufacturer.) NOTE: This does not prohibit incorporation of later nonconflicting revisions in the Pilot's Operating Handbook and FAA Approved Airplane Flight Manual. B) If the engines are equipped with AiResearch P/N 897110-8 fuel control assemblies, modify the airplaneand Pilot's Operating Handbook and FAA Approved Airplane Flight Manual in accordance with the following: 1) Adjust the Engine Fuel Controls and Computers in accordance with Garrett AiResearch Service Bulletin TPE 331-73-0093 and Cessna Customer Care Service Information Letter PJ 80-1. 2) Install a two-sided reversible instrument panel placard in accordance with Cessna Service Kit SK 441-28 and operate the airplane in accordance with this placard. 3) Perform an overspeed governor check in accordance with Cessna Service Kit SK 441-28. 4) Install Revision 8 in the Pilot's Operating Handbook and FAA Approved Flight Manual and operate the airplane in accordance with this revision. C) The airplane may be flown to a location where paragraphs A) or B) can be accomplished, provided it is not operated with aviation gasoline fuel, grades 80/87 or 100LL. D) Any equivalent method of compliance with this AD must be approved by the Chief, Engineering & ManufacturingDistrict Office No. 43, Federal Aviation Administration, Room 220, Mid-Continent Airport, Wichita, Kansas 67209. Telephone (316) 942-4285. Cessna Propjet Customer Care Service Information Letters PJ 79-8 dated April 2, 1979, and PJ 80-1 dated January 11, 1980, including Garrett AiResearch Service Bulletin TPE 331-73-0093, cover the subject matter of this AD. The AD supersedes AD 79-10-08, Amendment 39-3470 (44 FR 27977). This amendment becomes effective January 29, 1980.
2005-25-26: The FAA is adopting a new airworthiness directive (AD) for certain Boeing Model 747-400, 747-400D, and 747-400F series airplanes. This AD requires repetitive detailed inspections for damage (degraded finish; missing, lifted, peeling, or blistering paint; or signs of corrosion) of the interior skin in the forward and aft cargo compartments, and corrective actions if necessary. This AD results from reports of skin corrosion on four Boeing Model 747 series airplanes that were delivered between 1995 and 1999. We are issuing this AD to detect and correct corrosion, which can penetrate the thickness of the skin and cause cracking, and result in rapid decompression of the airplane.
2018-26-08: We are adopting a new airworthiness directive (AD) for certain Airbus SAS Model A320-214, A320-232, A320-233, A321-211 and A321-231 airplanes. This AD was prompted by an investigation that revealed that the outer cylinder of a certain ram air turbine (RAT) actuator was not properly deburred in accordance with manufacturing specifications. This AD requires a replacement of affected RAT actuators. We are issuing this AD to address the unsafe condition on these products.
98-26-04: This amendment supersedes an existing airworthiness directive (AD), applicable to certain Boeing Model 757 series airplanes, that currently requires an inspection of the engine fuel shutoff valves (spar valves) to detect leakage of fuel and to ensure that no leakage occurs when the valves are commanded to close. That amendment also requires an alignment procedure of the engine fuel shutoff valves, if necessary. This amendment expands the applicability of the existing AD. This amendment is prompted by additional reports that certain crossfeed valve assemblies and engine shutoff valve assemblies were improperly installed during manufacturing of the airplane. The actions specified in this AD are intended to prevent uncommanded fuel flow from the fuel tanks to the engine nacelle, which could result in reduced airplane fire protection in the event of a leak in the engine fuel line or a fire in the engine nacelle.
86-22-06: 86-22-06 CESSNA: Amendment 39-5453. Applies to Models 208 and 208A (Serial Numbers 20800001 thru 20800105) airplanes certificated in any category. Compliance: Required by December 31, 1986, unless already accomplished. To prevent fuel starvation during takeoff due to improper positioning of the wing fuel tank selectors, accomplish the following: (a) For Models 208 and 208A (Serial Numbers 20800001 through 20800105) airplanes, install the Cessna fuel selector warning system, revise the POH/AFM, and perform all required system checks, as described in Cessna Bulletin CAB86-8 dated October 10, 1986. (b) For Models 208 and 208A (Serial Numbers 20800001 through 20800083) airplanes, modify the low fuel level transmitter supports as described in Cessna Bulletin CAB 86- 26, dated September 5, 1986. (c) Airplanes may be flown in accordance with FAR 21.197 to a location where this AD may be accomplished. (d) An equivalent method of compliance with this AD may be approved by the Manager, Aircraft Certification Office, FAA, 1801 Airport Road, Room 100, Mid-Continent Airport, Wichita, Kansas 67209. All persons affected by this AD may obtain copies of the documents referred to herein upon request to Cessna Aircraft Company, Customer Services, Post Office Box 1521, Wichita, Kansas 67201; or FAA, Office of the Regional Counsel, Room 1558, 601 East 12th Street, Kansas City, Missouri 64106. This action supersedes AD 86-09-08, Amendment 39-5308, published May 12, 1986 (51 FR 17322) and withdraws NPRM Docket Number 86-CE-13-AD published June 5, 1986 (51 FR 20495). This amendment becomes effective on November 7, 1986.
2005-26-03: The FAA is adopting a new airworthiness directive (AD) for certain Boeing Model 737 airplanes. This AD requires modifying the elevator input torque tube assembly. This AD results from a report of a restriction in the pilot's elevator input control system. A design review performed on the elevator input torque tube assembly in the course of the investigation discovered possible failure modes that could lead to a jam of the elevator control system. We are issuing this AD to prevent loss of elevator control and consequent reduced controllability of the airplane.
2019-10-03: We are adopting a new airworthiness directive (AD) for all The Boeing Company Model 737-100, -200, -200C, -300, -400, and -500 series airplanes. This AD was prompted by reports of cracks caused by corrosion of the edge of the bore of the spot face and corrosion of the lug bore of certain side-strut support fitting lugs. This AD requires repetitive detailed inspections of the left and right side-strut support fitting lugs with bushings installed for any corrosion, any crack, or any severed lug; repetitive detailed and high frequency eddy current (HFEC) inspections of the left and right side-strut support fitting lugs with bushings removed for any corrosion or any crack; and applicable on-condition actions. We are issuing this AD to address the unsafe condition on these products.
98-24-33: This amendment adopts a new airworthiness directive (AD), applicable to certain McDonnell Douglas Model DC-9 and DC-9-80 series airplanes, Model MD-88 airplanes, and C-9 (military) series airplanes, that requires a one-time visual inspection to detect fatigue cracking of the lower left nose of certain longerons and the attaching frames; repair, if necessary; and installation of a preventive modification. This amendment is prompted by several reports of fatigue cracking of certain longerons and the attaching frames. The actions specified by this AD are intended to prevent such fatigue cracking, which could result in reduced structural integrity of the fuselage, and consequent loss of pressurization of the airplane.