Results
83-24-09: 83-24-09 DeHAVILLAND AIRCRAFT OF CANADA, LTD.: Amendment 39-4781. Applies to DeHavilland Model DHC-7 airplanes, Serial Numbers 3 through 92 inclusive. Compliance is required within the next 750 flight hours or three months after effective date of this AD, whichever occurs first, unless previously accomplished. To protect against loss of trimability and partial loss of pitch control, accomplish the following: 1. Incorporate Modification Number 7/2209 on each elevator and Modification Numbers 7/2211 and 7/2216 on the tailplane in accordance with instruction contained in DeHavilland Service Bulletin No. 7-55-6, Rev. B, dated September 17, 1982. 2. Alternate 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. 3. 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 as required by this AD. This amendment becomes effective December 21, 1983.
2019-24-12: The FAA is adopting a new airworthiness directive (AD) for certain De Havilland Aircraft of Canada Limited Model DHC-8-401 and - 402 airplanes. This AD was prompted by a report that certain fuselages were delivered with nonconforming keel tension fittings and stringer end fittings. This AD requires a detailed visual inspection of stringer end fittings and keel fittings for loose or working fasteners, signs of wear, and corrosion, and repair if necessary; and a general visual inspection of the keel tension fitting and stringer end fittings, as applicable, and repairs and replacement of the keel and stringer end fittings if necessary. The FAA is issuing this AD to address the unsafe condition on these products.
72-14-05: 72-14-05 PIPER: Amendment 39-1480 as amended by Amendment 39-1943. Applies to PA-23-250 and PA-E23-250 series aircraft Serial Nos. 27-2505 and up equipped with non-supercharged engine and certificated in all categories. Compliane required within the next 50 hours time in service after the effective date of this AD, unless already accomplished within the last 50 hours and thereafter at intervals not to exceed 100 hours. a. For airplanes Serial Nos. 27-7304959 and up, and earlier serial numbered aircraft which have field replacements, equipped with exhaust stack assemblies P/N's 33419-2, -3, 33420-2, -3 and stack support kit No. 760702, visually inspect both engine exhaust system stacks, manifolds, support tubes and brackets, and the slip joint inside the alternate air heat shroud. Inspect for cracks, flaking, burning, distortion and exhaust gas leaks at flanges and joints. Parts found cracked, flaked, burned, distorted or which allow leakage must be replaced prior to further flight. b. For airplanes Serial Nos. 27-2505 to 27-7304958 inclusive equipped with original type exhaust system configuration or field replacement components as listed under Piper Service Letter No. 533, Service Spares Letter No. SP-301 or Service Bulletin No. 319: Visually inspect in accordance with a. above and adjust and align ball joint stack assemblies and supports in accordance with Piper Service Bulletin No. 319 dated April 19, 1971 or later approved revision. c. Equivalent inspections or modifications may be approved by the Chief, Engineering and Manufacturing Branch, FAA Eastern Region. Aircraft may be flown to a base where the maintenance required by this airworthiness directive may be performed as permitted by FAR's 21.197 and 21.199. (Piper Service Spares Letter No. SP-301 dated November 11, 1969, and Service Bulletin No. 319 dated April 19, 1971, pertain to this subject) Amendment 39-1480 supersedes AD 69-23-01. Amendment 39-1480 was effective July 12, 1972. This Amendment 39-1943 is effective September 3, 1974.
80-17-12: 80-17-12 MCDONNELL DOUGLAS: Amendment 39-3890. Applies to DC-10 Series Airplanes fuselage numbers 1 through 243. \n\n\tCompliance required as indicated, unless already accomplished. To prevent restriction of travel of the wing engine emergency fire shut off handle and loss of associated fire fighting safeguards, accomplish the following: \n\n\tWithin 300 hours additional time in service after the effective date of this AD, accomplish paragraph (1) or (2) below. \n\n\t(1)\tInspect and seal cable guard pin P/N AA 2603-9 in place in accordance with McDonnell Douglas Alert Service Bulletin A76-27 dated 6/24/80 and within 1500 hours additional time in service after the effective date of this AD accomplish the modification described in McDonnell Douglas Service Bulletin 76-27 dated 7/16/80; or \n\n\t(2)\tAccomplish the modification described in McDonnell Douglas Service Bulletin 76-27 dated 7/16/80. \n\n\t(3)\tAccomplishment of the modification described in McDonnell Douglas Service Bulletin 76-27 dated 7/16/80 is terminating action for this AD. Service Bulletin 76-27 calls for the replacement of the existing guard pin with a new guard pin incorporating a lip retaining head. \n\n\t(4)\tSpecial flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate airplanes to a base for the accomplishment of modification required by this AD. \n\n\t(5)\tAlternative 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. \n\n\tThis amendment becomes effective August 28, 1980.
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.