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.
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.
2019-24-15: The FAA is adopting an airworthiness directive (AD) for certain The Boeing Company Model 737-900ER series airplanes. This AD requires replacement of nonconforming head strike pads with conforming head strike pads. This AD was prompted by a report of nonconforming head strike pads on the left and right mid exit doors. The FAA is issuing this AD to address the unsafe condition on these products.
74-14-06: 74-14-06 PIPER: Amendment 39-1885. Applies to all Model PA-36-285 airplanes, S/N 36-7360001 through 36-7460016 certificated in all categories. Compliance required within the next 25 hours time in service after the effective date of this AD unless already accomplished. To preclude the possibility of having bolts installed in the wing spar carry through assembly which could be subject to deformation, accomplish the following: (a) Remove a total of four AN 4C-11A bolts and corresponding nuts and washers from the spar center section carry through left and right end vertical stiffeners. (b) Enlarge these four holes to 5/16" + .005 - .001 diameter. If the maximum hole size above does not eliminate evidence of elongation or wear, damaged parts should be replaced or further repaired in a method approved by the Chief, Engineering and Manufacturing Branch, FAA Southern Region. (c) Install an AN5-11A bolt, AN960-516L washer under bolt head, MS20365-524C nut and anAN960-516 washer under nut in each of the four holes. Torque to 100-140 inch pounds. Piper Service Bulletin No. 425 pertains to this same subject. This amendment becomes effective July 8, 1974.
2007-20-08: We are adopting a new airworthiness directive (AD) for the products listed above. This AD results from mandatory continuing airworthiness information (MCAI) issued by an aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as: To prevent fuel system leaks inspect the bronze/brass hollow threaded fuel line fittings for type and leaks, per Avions Pierre Robin Service Bulletin (SB) No. 86. We are issuing this AD to require actions to correct the unsafe condition on these products.
82-12-05: 82-12-05 ROLLS-ROYCE, LTD.: Amendment 39-4398. Applies to Rolls-Royce, Ltd., RB211-22B and -524 series turbofan model engines. Compliance required as indicated unless already accomplished. To preclude possible loss of the fan assembly, install the Rolls-Royce axial fan retention modification as specified in Rolls-Royce Service Bulletin 72-6574, Revision 2, dated March 19, 1982, or later revision approved by the FAA, applicable to RB211-22B, -524B-02, -524B2-19, -524B2-39, and -524C2-19 engines and as specified in Rolls-Royce Service Bulletin 72-6576, Revision 2, dated March 19, 1982, or later revision approved by the FAA, applicable to RB211-524B3-02, -524B4-02, and -524D4-19 engines in accordance with the following schedule: 1. Center (fuselage mounted) engines on Lockheed L1011 aircraft by September 30, 1982. 2. Wing mounted engines on Lockheed L1011 and Boeing B747 by December 31, 1982. All persons affected by this directive who have not already received the referenced service bulletins from the manufacturer may obtain copies upon request to Technical Publications Department, Rolls-Royce, Ltd., P.O. Box 31, Derby, England DE2 8BJ. This document may also be examined at Federal Aviation Administration, New England Region, 12 New England Executive Park, Burlington, Massachusetts 01803. A historical file on this AD is maintained by the FAA at the New England Regional Office. Upon request of the operator, an FAA Maintenance Inspector, subject to prior approval of the Chief, Aircraft Certification Division, FAA, New England Region, may adjust the compliance date(s) specified in this AD to permit compliance at an established inspection period of the operator if the request contains substantiating data to justify the adjustment for that operator. This amendment becomes effective June 7, 1982.
2019-24-11: The FAA is superseding Airworthiness Directive (AD) 2014-16-26 and AD 2017-19-04, which applied to certain Dassault Aviation Model FALCON 900EX airplanes. Those ADs required revising the existing maintenance or inspection program, as applicable, to incorporate new or more restrictive maintenance requirements and/or airworthiness limitations. Since the FAA issued AD 2014-16-26 and AD 2017-19-04, the FAA determined that new or more restrictive airworthiness limitations are necessary. This AD continues to require those maintenance or inspection program revisions, and also requires revising the existing maintenance or inspection program, as applicable, to incorporate additional new or more restrictive airworthiness limitations. The FAA is issuing this AD to address the unsafe condition on these products.
74-09-04: 74-09-04 PIPER: Amendment 39-1821. Applies to Model PA-28-140 Serial Numbers 28-7225001 through 28-7325674; Model PA-28-180 Serial Numbers 28-7205001 through 28- 7305601; Model PA-28-235 Serial Numbers 28-7210001 through 28-7310176; and Model PA- 28R-200 Serial Numbers 28R-7235001 through 28R-7335446, certificated in all categories. Compliance required within the next 100 hours time in service from the effective date of this AD, unless already accomplished. To provide a safer rear seat belt installation, accomplish the following: Relocate the rear seat safety belt outboard attachments in accordance with Piper Service Bulletin Number 393 or equivalent approved by the Chief, Engineering and Manufacturing Branch, Federal Aviation Administration, Southern Region, Atlanta, Georgia. The manufacturer's specifications and procedures identified and described in this directive are incorporated herein and made apart hereof pursuant to 5 U.S.C. 552(a)(1). All persons affected by this directive who have not already received these documents from the manufacturer may obtain copies upon request to Piper Aircraft Corporation, Vero Beach Division, Vero Beach, Florida 32960. These documents may also be examined at the Federal Aviation Administration, Southern Region, 3400 Whipple Street, East Point, Georgia 30344 and at Federal Aviation Administration Headquarters, 800 Independence Avenue, S.W., Washington, D.C. A historical file on this AD which includes the incorporated material in full is maintained by the FAA at its Headquarters in Washington, D.C., and at the Federal Aviation Administration, Southern Region. This amendment becomes effective April 24, 1974.
88-24-02: 88-24-02 PRATT & WHITNEY CANADA (PWC): Priority letter AD issued November 16, 1988. Applies to PT6A-50 turboprop engines installed on Dehavilland of Canada DHC-7 aircraft. This priority letter AD is effective immediately upon receipt. Compliance is required as indicated, unless already accomplished. To prevent uncontained PT blade failure resulting from a PT blade shed overspeed event due to a RG assembly failure, accomplish the following: (a) Within one calendar day after receipt of this priority letter AD, inspect the airframe chip detector flag system and reinspect each day of operation, in accordance with Dehavilland Canada Dash 7 Maintenance Manual, Section 71-05-00. If the chip detector flag is actuated, accomplish paragraphs (b) (1), (b)(2), and (b) (4), of this AD, prior to further flight. (b) Within the next 50 hours in service after receipt of this priority letter AD, accomplish the following, unless already accomplished: (1) Remove and visually inspectthe engine chip detector for metal debris, in accordance with PWC PT6A-50 Maintenance Manual, Section 79-35-02, and based on the inspection results, accomplish the applicable procedures specified in Section 79-35-02. (2) Remove from service chip detector Part Number (P/N) 3020019, if installed, and replace with chip detector P/N 3026609. (3) Inspect the circuit wiring of the installed or replacement chip detector, P/N 3026609 in accordance with PWC PT6A-50 Maintenance Manual, Section 79-35-02. Remove from service, prior to further flight, chip detectors found with an open circuit and replace with serviceable parts. (4) Perform a one time-inspection check of the airframe chip detector flag system by grounding the wiring pins in the connector to the chip detector, in accordance with PWC Alert Service Information Letter (SIL) No. 4019, dated October 20, 1988. If chip detector flag is not actuated in the nacelle, correct defects, and repeat this inspection check until the chip detector flag actuation is confirmed (reference DeHavilland Canada Dash 7 Maintenance Manual, Section 71-05-00, dated July 15, 1977). (5) Inspect the main oil filter for contamination and, based on the inspection results, accomplish the applicable procedures specified in PWC PT6A-50 Maintenance Manual, Section 79-25-04. (c) Reinspect the main oil filter, thereafter, at intervals not to exceed 100 hours in service since last inspection in accordance with the requirements of paragraph (b) (5) above. If visible metallic debris is evident, accomplish paragraph (b) (1) above prior to further flight. (d) Remove, inspect, and reinstall the chip detector of non-installed engines, in accordance with paragraphs (b) (1), (b) (2), and (b) (3) above, prior to entering service. (e) Aircraft may be ferried in accordance with the provisions of Federal Aviation Regulations 21.197 and 21.199 to a base where the priority letter AD can be accomplished. (f) Upon request, an equivalent means of compliance with the requirements of this priority letter AD may be approved by the Manager, Engine Certification Office, Engine and Propeller Directorate, Aircraft Certification Service, Federal Aviation Administration, 12 New England Executive Park, Burlington, Massachusetts 01803. (g) Upon submission of substantiating data by an owner or operator through an FAA Airworthiness Inspector, the Manager, Engine Certification Office, Engine and Propeller Directorate, Aircraft Certification Service, may adjust the compliance times specified in this priority letter AD. The applicable engine manufacturer's alert SIL No. 4019 and Maintenance Manual, Sections 79-35-02 and 79-25-04, may be obtained from Pratt & Whitney Canada, 1000 Marie-Victorin, Longueuil, Quebec, Canada J4G 1A1. The applicable aircraft Maintenance Manual, Section 71-05-00, may be obtained from Boeing Canada, DeHavilland Division, Garrett Boulevard, Downsview, Ontario, Canada M3K 145. The documents referenced inthis priority letter AD also may be examined at the Office of the Assistant Chief Counsel, Federal Aviation Administration, New England Region, 12 New England Executive Park, Burlington, Massachusetts 01803, Room 311, Rules Docket No. 88-ANE-38, between the hours of 8:00 a.m. and 4:30 p.m. Monday through Friday except federal holidays. This priority letter AD 88-24-02 is effective immediately upon receipt.
2019-24-17: The FAA is adopting a new airworthiness directive (AD) for all The Boeing Company Model MD-90-30 airplanes. This AD was prompted by reports indicating that certain center wing stringers and skins are potentially susceptible to cracking. This AD requires repetitive eddy current, low frequency (ETLF) inspections of the left and right side fastener holes for any crack; repetitive eddy current, high frequency (ETHF) inspections of the lower skin for any crack; and repair if any crack is found. The FAA is issuing this AD to address the unsafe condition on these products.
99-01-17: This amendment adopts a new airworthiness directive (AD), applicable to certain Airbus Model A320 series airplanes, that requires repetitive inspections to detect fatigue cracking in certain areas of the fuselage; and corrective action, if necessary. This amendment also provides for an optional terminating action for the repetitive inspections. 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 detect and correct fatigue cracking of the fuselage, which could result in reduced structural integrity of the airplane.
2021-09-16: The FAA is adopting a new airworthiness directive (AD) for certain Bombardier, Inc., Model BD-100-1A10 airplanes. This AD was prompted by a report of a number of low altitude engine surge incidents during takeoff. This AD requires revising the existing airplane flight manual and applicable corresponding operational procedures to provide the flightcrew with procedures to require the engine bleeds to be ''ON'' during takeoff. The FAA is issuing this AD to address the unsafe condition on these products.
74-09-02: 74-09-02 PIPER: Amendment 39-1816. Applies to Model PA-32-260 Airplanes, Serial Numbers 32-7300001 through 32-7300024 and Model PA-32-300, Serial Numbers 32-7340001 through 32-7340081, certificated in all categories. Compliance required within the next 100 hours time in service after the effective date of this AD, unless already accomplished. To provide an unobstructed view of the stall warning light, accomplish the following: Relocate stall warning light in accordance with Piper Service Bulletin Number 403 or in an equivalent manner approved by the Chief, Engineering and Manufacturing Branch, Federal Aviation Administration, P.O. Box 20636, Atlanta, Georgia 30320. The manufacturer's specifications and procedures identified and described in this directive are incorporated herein and made a part hereof pursuant to 5 U.S.C. 522(a)(1). All persons affected by this directive who have not already received these documents from the manufacturer may obtain copies upon request to Piper Aircraft Corporation, Vero Beach Division, Vero Beach, Florida 32960. These documents may also be examined at the FAA, Southern Region, 3400 Whipple Avenue, East Point, Georgia 30344 and at FAA Headquarters, 800 Independence Avenue, S.W., Washington, D.C. A historical file on this AD which includes the incorporated material in full is maintained by the FAA at its headquarters in Washington, D.C., and at the FAA, Southern Region office. This amendment becomes effective April 18, 1974.