Results
2007-21-08: The FAA is adopting a new airworthiness directive (AD) for certain Hawker Beechcraft Model Hawker 800XP airplanes. This AD requires doing an inspection of panel DA wiring for clearance and for signs of chafing or exposed conductors, and repairing or replacing the wires and cable ties if necessary. This AD results from reports of wire bundle interference in the DA panel, chafed wire bundles, and exposed conductors. We are issuing this AD to prevent chafing of wire bundles, which could cause an electrical short and consequent loss of several functions essential for safe flight and smoke or fire in the flight compartment and main cabin.
83-24-03: 83-24-03 BOEING: Amendment 39-4774. Applies to Model 707 and 720 series aircraft certificated in all categories. Accomplish the following within 120 days after the effective date of this AD, unless already accomplished within the last 21 months, and at intervals thereafter not to exceed 24 months: \n\n\tA.\tVisually inspect the lower rudder tab control rod assemblies, including all dash numbers, which have been in service more than 5 years, in accordance with Boeing Service Bulletin 3424, dated July 1, 1983, or later FAA approved revisions. \n\n\tB.\tReplace any rod assembly exhibiting cracks or corrosion with a new or reconditioned rod assembly.\n \n\tC.\tAlternate means of compliance which provide an equivalent level of safety may be used when approved by the Manager, Seattle Aircraft Certification Office, FAA, Northwest Mountain Region. \n\n\tD.\tAircraft may be ferried to a base for maintenance in accordance with Section 21.197 and 21.199 of the Federal Aviation Regulations. \n\n\tE.Upon request of the operator, an FAA Maintenance Inspector, subject to prior approval of the Manager, Seattle Aircraft Certification Office, FAA, Northwest Mountain Region, may adjust the repetitive inspection intervals specified in this AD to permit compliance at an established inspection period of an operator, if the request contains substantiating data to justify the adjustment period. \n\n\tAll persons affected by this directive who have not already received these documents from the manufacturer may obtain copies upon request to Boeing Commercial Airplane Company, P.O. Box 3707, Seattle, Washington 98124. These documents may also be examined at the FAA, Northwest Mountain Region, 9010 East Marginal Way South, Seattle, Washington. \n\n\tThis amendment becomes effective January 3, 1984.
2021-08-02: The FAA is adopting a new airworthiness directive (AD) for all Safran Helicopter Engines, S.A. (Safran) Arriel 2D and Arriel 2E model turboshaft engines. This AD was prompted by the manufacturer revising the maintenance and overhaul manuals to introduce new or more restrictive airworthiness limitations and maintenance tasks. This AD requires the replacement of certain critical parts before reaching their published in-service life limits, performing scheduled \n\n((Page 26652)) \n\nmaintenance tasks before reaching their published periodicity, and performing unscheduled maintenance tasks when the engine meets certain conditions. As a terminating action, this AD requires operators to revise the airworthiness limitation section (ALS) of their existing approved aircraft maintenance program (AMP) by incorporating the revised airworthiness limitations and maintenance tasks. The FAA is issuing this AD to address the unsafe condition on these products.
2007-21-13: The FAA is adopting a new airworthiness directive (AD) for certain Boeing Model 747 and 767 airplanes. This AD requires reworking the electrical bonding between the airplane structure and the pump housing of the outboard boost pumps in the main fuel tank of certain Boeing Model 747 \nairplanes, and between the airplane structure and the pump housing of the override/jettison pumps in the left and right wing center auxiliary fuel tanks of certain Boeing Model 767 airplanes. This AD also requires related investigative actions and corrective actions if necessary. This AD results from fuel system reviews conducted by the manufacturer. We are issuing this AD to prevent insufficient electrical bonding, which could result in a potential of ignition sources inside the fuel tanks, and which, in combination with flammable fuel vapors, could result in fuel tank explosions and consequent loss of the airplane.
74-17-08: 74-17-08 PIPER: Amendment 39-1918. Applies to PA-34-200 airplanes Serial Numbers 34-7250001 to 34-7450209 inclusive, certificated in all categories. Compliance required within the next 50 hours' time in service after the effective date of this AD, unless already accomplished. To prevent fuel line chafing and fuel leaks, accomplish the following: Modify the fuel and instrumentation line clamping in accordance with Piper Service Bulletin No. 429 or an equivalent method approved by the Chief, Engineering and Manufacturing Branch, Federal Aviation Administration, Southern Region. Replace all lines that have been damaged by chafing, wear, with serviceable lines of the same part number or equivalent lines approved by the Chief, Engineering and Manufacturing Branch, Federal Aviation Administration Southern Region. This amendment becomes effective August 15, 1974.
79-09-02: 79-09-02 CESSNA: Amendment 39-3453. Applies to Model 441 (Serial Numbers 441-0001 through 441-0090) airplanes. COMPLIANCE: Required as indicated, unless already accomplished. To assure proper drainage of the aileron control surfaces, within the next 100 hours time-in-service after the effective date of this AD, accomplish the following: A) Incorporate additional drainage of the ailerons by drilling new drain holes in accordance with the instructions provided in Cessna Propjet Service Information Letter PJ 79-3, dated March 5, 1979. B) Any equivalent method of compliance with this AD must be approved by the Chief, Engineering and Manufacturing Branch, FAA, Central Region. NOTE: The FAA has determined that there is insufficient justification to require mandatory compliance with the elevator portion of Cessna Service Information Letter PJ 79-3. Therefore, this AD is not applicable to elevator drainage improvements provided by that letter. This Amendment becomes effective May 7, 1979.
2019-24-14: The FAA is adopting a new airworthiness directive (AD) for certain 328 Support Services GmbH Model 328-100 airplanes. This AD was prompted by a report of missing rivets on landing flap support arm 2. This AD requires an inspection of the landing flap support arms for missing rivets and corrective actions if necessary, 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.
74-16-08: 74-16-08 PIPER: Amendment 39-1912. Applies to Model PA-30 and Model PA-39 aircraft certificated in all categories except aircraft incorporating Piper Kit Part Number 760 783. Compliance required as indicated. To prevent possible hazards in flight associated with cracking of the aft bulkhead assembly, fuselage station 258, accomplish the following: 1. Within the next 50 hours in service from the effective date of this AD, unless already accomplished within the past 50 hours in service, and at intervals not to exceed 100 hours in service from the last inspection, inspect in accordance with paragraph 2. 2. Remove the tail cone and visually inspect, with five times power minimum magnification, the aft bulkhead assembly, fuselage station 258, Part Number 22893-00 on Model PA-30 and Model PA-39, Serial Nos. 39-1 through 39-83 or Part Number 22893-06 on Model PA-39, Serial Nos. 39-84 and up, for cracks in the area of the aft fin attachment brackets. 3. If cracks aredetected, repair in accordance with Fin Attachment Bracket Installation Kit, Piper Part Number 760 783 or equivalent prior to further flight, except that the airplane may be flown in accordance with FAR 21.197 to a base where a repair can be made. 4. Upon incorporation of the Fin Attachment Bracket Installation Kit, Piper Part Number 760 783 or equivalent, compliance with the requirements of this AD may be dispensed with. 5. Equivalent repairs must be approved by the Chief, Engineering and Manufacturing Branch, FAA, Eastern Region. 6. Upon submission of substantiating data by an owner or operator through an FAA Maintenance Inspector, the Chief, Engineering and Manufacturing Branch, FAA, Eastern Region, may adjust the repetitive inspection interval specified in this AD. (Piper Service Letter No. 679 refers to this subject.) This amendment is effective August 9, 1974.
80-03-05 R1: 80-03-05 R1 ROCKWELL INTERNATIONAL: Amendment 39-3685 as amended by Amendment 39-3772. Applies to Model NA-265-70 serial numbers 1 and 7 only, and NA-265-80 (all) series airplanes certificated in all categories. Compliance required as indicated, unless already accomplished. To prevent elevator trailing edge delamination, accomplish the following: a. Within 15 hours' time in service or 10 days from the effective date of this AD, whichever occurs first, inspect elevator trailing edge for delamination as specified in paragraph 7, "Modification Instructions" of Rockwell International, Sabreliner Division, Service Bulletin No. 43 dated September 14, 1979. b. If evidence of delamination is found, prior to further flight, accomplish paragraph (d) of this AD. c. If no evidence of delamination is found, prior to the accumulation of 300 additional hours' time in service or 90 days from the effective date of this AD, whichever occurs first, accomplish paragraph (d) ofthis AD. d. Repair any delamination, enlarge existing 25 drain holes and add 75 drain holes as specified in "Modification Instructions" of Service Bulletin No. 43, and add elevator balance weights and accomplish static balance check as specified in Rockwell International, Sabreliner Division, Service Bulletin No. 44 dated September 14, 1979. e. Alternative inspections, modifications or other actions which provide an equivalent level of safety may be used when approved by the Chief, Aircraft Engineering Division, FAA Western Region. f. 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 required by this AD. Amendment 39-3685 became effective February 11, 1980. This Amendment 39-3772 becomes effective May 29, 1980.
79-05-07: 79-05-07 GULFSTREAM AMERICAN (Formerly Grumman American Aviation Corporation): Amendment 39-3424. Applies to Model GA-7 airplanes, certificated in all categories, serial numbers GA7-0002 through GA7-0009, GA7-0011 through GA7-0057, and GA7-0059. Compliance is required within the next 25 hours' time in service after the effective date of this AD, unless already accomplished. To detect and prevent fuel leakage from cracks in the inboard fuel tank ribs at Wing Station (W.S.) 109, at the forward fuel tank outlet fittings in the left and right wings, accomplish the following: (a) Inspect, repair, and modify these aircraft in accordance with Gulfstream American Service Bulletin No. ME-9, dated November 13, 1978, and Supplement No. 1 dated December 18, 1978, or later revision approved by the Chief, Engineering and Manufacturing Branch, FAA, Southern Region. In accomplishing the repair instructions of the service bulletin the additional defueling safety practices containedin GA-7 Maintenance Manual, Section 28-0, page 201, Fuel System-Maintenance Policies, must be observed. (b) Equivalent methods of compliance with this AD may be acceptable if approved by the Chief, Engineering and Manufacturing Branch, FAA, Southern Region. (c) Airplanes may be flown in accordance with FAR 21.197 to a location where the needed inspection and repairs and fuel line replacement required by this AD may be accomplished. This amendment becomes effective March 9, 1979.