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91-13-08: 91-13-08 ISRAEL AIRCRAFT INDUSTRIES (IAI): Amendment 39-7039. Docket No. 91-NM-32- AD. Applicability: Models 1121, 1121A, 1121B, 1123, 1124, and 1124A series airplanes, certificated in any category. Compliance: Required within 60 days after the effective date of this AD, unless previously accomplished. To prevent the inability to extend the nose landing gear for landing, accomplish the following: A. Remove the existing towing instruction placard and install a new placard in accordance with the applicable service bulletin, as follows: Airplane Models Service Bulletin 1121, 1121A, 1121B 1121-11-015, dated November 26, 1990 1123 1123-11-031, dated November 26, 1990 1124 and 1124A 1124-11-103, dated November 26, 1990 B. An alternative method of compliance or adjustment of the compliance time, which provides an acceptable level of safety, may be used when approved by the Manager, Standardization Branch, ANM- 113, FAA, Transport Airplane Directorate.NOTE: The request should be forwarded through an FAA Principal Maintenance Inspector, who may concur or comment and then send it to the Manager, Standardization Branch, ANM-113. C. Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate airplanes to a base in order to comply with the requirements of this AD. All persons affected by this directive who have not already received the appropriate service documents from the manufacturer may obtain copies upon request to Astra Jet Corporation, Technical Publications, 77 McCullough Drive, Suite 11, New Castle, Delaware 19720. These documents may be examined at the FAA, Northwest Mountain Region, Transport Airplane Directorate, 1601 Lind Avenue S.W., Renton, Washington. This amendment (39-7039, AD 91-13-08) becomes effective on July 22, 1991.
72-14-01: 72-14-01 DOWTY ROTOL, LTD: Amdt. 39-1473. Applies to Dowty Rotol Propeller Types (c)R130/4-20-4/12E, (c)R186/4-30-4/16, (c)R187/4-30-4/18, (c)R193/4-30-4/50, (c)R184/4-30-4/50, (c)R259/4-40-4.5/17, (c)R148/4-20-4/21E, (c)R175/4-30-4/13E, (c)R179/4- 20-4/33, (c)R257/4-30-4/60, (c)R245/4-40-4.5/13, and (c)R209/4-40-4.5/2. These propellers are installed on, but not necessarily limited to, BAC Viscount Models 744, 745D, and 810; Armstrong Whitworth Model Argosy AW.650 Series 101; Fairchild and Fokker Models F27 and F227; Handley Page Model Herald; and Grumman Model Gulfstream G-159 airplanes. Compliance is required as indicated unless already accomplished. To prevent failure of a propeller blade due to the disengagement of the blade bearing retaining bolts resulting from excessive wear on the teeth of the locking segments, accomplish the following: Within the next 5,000 hours' time in service or at the next propeller overhaul, after the effective date of this AD, whichever occurs sooner, incorporate Dowty Rotol Modification No. (c) VP.2676 (Rev. 1) in accordance with Dowty Rotol Limited Service Bulletin No. 61-714, Revision 3, dated July 26, 1971, or an FAA-approved equivalent. This amendment becomes effective 22 July, 1972.
91-16-01: 91-16-01 MITSUBISHI HEAVY INDUSTRIES (MHI), LTD. [formerly Nihon Aeroplane Manufacturing Company (NMAC)]: Amendment 39-7091. Docket No. 91-NM-118-AD. Supersedes AD 91-06-04. Applicability: Model YS-11, YS-11A-200, YS-11A-300, YS-11A-500, and YS-11A-600 series airplanes, certificated in any category. Compliance: Required as indicated, unless previously accomplished. To prevent uncontrolled nose down pitch of the airplane on landing approach during icing conditions, accomplish the following: (a) Within 30 days after March 19, 1991 (the effective date of Amendment 39-6922, AD 91- 06-04), accomplish the following: (1) Revise the Operating Limitations Section of the FAA-approved Airplane Flight Manual (AFM) for the Model YS-11/-11A by adding a subparagraph B. to paragraph 1.10.5, WING DE- ICER SYSTEM, to read as follows: This may be accomplished by inserting a copy of this AD in the AFM. "B. Do not extend flaps greater than 20 degrees in the presence of known icing conditions or in visible moisture below plus 5 degrees centigrade (plus 41 degrees Fahrenheit) outside air temperature (OAT)." (2) Add a placard as near as possible to the flap handle to read as follows: "Flaps limited to 20 degrees in known icing conditions." (b) Within 30 days after the effective date of this amendment, accomplish the following: (1) Insert the following MHI Transmittal Letters in the Normal Operating Procedures Section of the AFM, as applicable: (i) For Model YS-11 airplanes: NMAC YS-11 Flight Manual Publication No. YS-FM-001, Transmittal Letter E32, dated October 2, 1990; (ii) For Model YS-11A-200 and -300 series airplanes: NMAC YS-11A- 200/300 Flight Manual Publication No. YS-FM-002, Transmittal Letter No. E2027, dated October 2, 1990; (iii) For Model YS-11A-500 series airplanes: NMAC YS-11A-500 Flight Manual Publication No. YS-FM-005, Transmittal Letter No. E5021, dated October 2, 1990; (iv) For ModelYS-11A-600 series airplanes: NMAC YS-11A-600 Flight Manual Publication No. YS-FM-006, Transmittal Letter No. E6021, dated October 2, 1990. (2) In the Normal Operating Procedures Section of the AFM, just after the MHI Transmittal Letter required by paragraph (b)(1) of this AD, revise subparagraph "(2) Flaps" of paragraph 3.1.10.1, APPROACH AND LANDING IN ICING CONDITIONS OR IN VISIBLE MOISTURE BELOW plus 5 DEGREES C (plus 41 DEGREES F) OAT, to read as follows: This may be accomplished by inserting a copy of this AD in the AFM. "(2) Flaps.............................................Set Position NOTE: Do not extend flaps greater than 20 degrees. CAUTION: IF UNUSUAL PITCHING OR YOKE MOVEMENT OCCURS WHILE EXTENDING THE FLAPS, IMMEDIATELY RETRACT THE FLAPS UNTIL THE PITCHING OR YOKE MOVEMENT STOPS." (c) An alternative method of compliance or adjustment of the compliance time, which provides an acceptable level of safety, may be used when approved by the Manager, Los Angeles Aircraft Certification Office (ACO), FAA, Transport Airplane Directorate. NOTE: The request should be forwarded through an FAA Principal Maintenance Inspector, who may concur or comment and then send it to the Manager, Los Angeles ACO. NOTE: Previous FAA approval granted for an alternative method of compliance with AD 91-06- 04 constitutes FAA approval as an alternative method of compliance with this AD. (d) Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate airplanes to a base in order to comply with the requirements of this AD. (e) The AFM revision requirements shall be accomplished, in part, by incorporating the following documents into the AFM: NMAC YS-11 Flight Manual Publication No. YS-FM-001, Transmittal Letter E32; NMAC YS-11A-200/300 Flight Manual Publication No. YS-FM-002, Transmittal Letter No. E2027; NMAC YS-11A-500 Flight Manual Publication No. YS-FM-005, Transmittal Letter No. E5021; NMAC YS-11A-600 Flight Manual Publication No. YS-FM-006, Transmittal Letter No. E6021; all of which are dated October 2, 1990. These documents contain the following list of effective pages: Publication Number/ Transmittal Letter Number Section Code Symbol Page Number Publication No. YS-FM-001 Transmittal Letter E32, dated October 2, 1990 Transmittal Sheet L.E.P. Log of Revision (1) 3 T/L E32 (none) (none) (none) (none) (none) 1/1 i ii-10 i 25 25a Publication No. YS-FM-002 Transmittal Letter E2027 dated October 2, 1990 Transmittal Sheet L.E.P. Log of Revision (1) 3 T/L E2027 E101 E101 E100 E100 E100 1/1 i ii-8 i 21 22 Publication No. YS-FM-005 Transmittal Letter E5021 dated October 2, 1990 Transmittal Sheet L.E.P. Log of Revision (1) 3 T/L E5021 E500 E156 E100 E100 E100 1/1 i ii-5 i 21 22 Publication No. YS-FM-006 Transmittal Letter E6021 dated October 2, 1990 Transmittal Sheet L.E.P. Log of Revision (1) 3 T/LE6021 E600 E156 E100 E100 E100 1/1 i ii-5 i 21 22 This incorporation by reference was approved by the Director of the Federal Register in accordance with 5 U.S.C. 552(a) and 1 CFR Part 51. Copies may be obtained from Nagoya Aircraft Works, Mitsubishi Heavy Industries, Ltd., 10 Oye-cho, Minato-Ku, Nagoya 455, Japan, Attention: Manager, YS-11 Group, Service Department. This information may be examined at the FAA, Northwest Mountain Region, Transport Airplane Directorate, 1601 Lind Avenue S.W., Renton, Washington; or at the Los Angeles Aircraft Certification Office, 3229 East Spring Street, Long Beach, California; or at the Office of the Federal Register, 1100 L Street N.W., Room 8401, Washington, D.C. Airworthiness Directive 91-16-01 supersedes AD 91-06-04, Amendment 39-6922. This amendment (39-7091, AD 91-16-01) becomes effective on August 22, 1991.
2022-21-16: The FAA is adopting a new airworthiness directive (AD) for certain Gulfstream Aerospace LP Model Gulfstream G150 airplanes. This AD was prompted by reports that wing flap fairing debonding and corrosion were discovered at certain areas of the lower skin on both wings. This AD requires an inspection for corrosion in certain areas of the wing skin fairings, additional inspections if necessary, resealing the fairings with new fillet seal, and applicable corrective actions, as specified in a Civil Aviation Authority of Israel (CAAI) AD, which is incorporated by reference. The FAA is issuing this AD to address the unsafe condition on these products.
2004-22-04: This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 747-400, -400D, and -400F series airplanes, equipped with GE or P&W series engines. This amendment requires modifications and functional tests of the wiring of the wire integration unit and the air supply control test unit (ASCTU) of the engine bleed air distribution system. The actions specified by this AD are intended to prevent inadvertent commanded shutdown of the engine bleed air distribution systems due to an erroneous ASCTU command. This type of shutdown could cause depressurization of the airplane and subsequent ice build-up on the engine inlets during descent, which could result in ingestion of ice into the engine(s) and consequent loss of thrust on one or more engines. This action is intended to address the identified unsafe condition.
72-19-02: 72-19-02 PITTS AVIATION ENTERPRISES, INC: Amdt. 39-1518. Applies to the Pitts Model S-2A Series Airplanes, S/N 2001 through 2025. Compliance required within the next 10 hours time in service after the effective date of this AD, unless already accomplished. To prevent structural damage because of excessive in-flight vibration of the aileron interconnect tubes, accomplish the following: (a) Remove streamline aileron interconnect tubes, P/N 2-5216-1. NOTE: Make certain the length between the AN3 bolt centers for the upper and lower aileron attachments of the interconnect tube are not changed during removal. (b) Install round aileron interconnect tubes, P/N 2-5216-11. When installing the replacement tubes, make certain to adjust the length of the lower threaded end to the same overall length between AN3 bolt centers as the tubes originally installed on your airplane. Make certain that the correct number of AN960-10 (1/16 or 1/32 inch thick) washers are installed so that the bearing inner races are clamped-up snugly without bending the fork ends of the tubes. Pitts Service Bulletin No. 5, including Supplement No. 1, pertains to this same subject. This amendment becomes effective September 15, 1972.
2004-22-06: This amendment adopts a new airworthiness directive (AD), applicable to certain Dornier Model 328-100 and -300 series airplanes, that requires inspection of the metal oxide varistor (MOV) modules and transient absorption zener (TAZ) diodes to determine if those parts are outside of tolerance limits, and replacement of MOV modules and TAZ diodes with new parts, if necessary. This action is necessary to prevent the failure of critical ice protection systems following a lightning strike, which could result in reduced controllability and degraded performance of the airplane in the event of an encounter with icing conditions. This action is intended to address the identified unsafe condition.
2022-22-01: The FAA is adopting a new airworthiness directive (AD) for certain Airbus SAS Model A350-941 airplanes. This AD was prompted by a report that the path for the grounding wire of the engine fire shut off valve (FSOV) is routed through the wing trailing edge, which is not the shortest path available. This AD requires modifying the wiring between the inboard fixed leading edge in the wing and in the forward cargo compartment on the left- and right-hand sides, 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.
2013-15-04: We are adopting a new airworthiness directive (AD) for certain Hartzell Propeller, Inc. propeller models HC-(1,D)2(X,V,MV)20-7, HC- (1,D)2(X,V,MV)20-8, and HC-(1,D)3(X,V,MV)20-8. This AD was prompted by failures of the propeller hydraulic bladder diaphragm and resulting engine oil leak. This AD requires replacement of the propeller hydraulic bladder diaphragm. We are issuing this AD to prevent propeller hydraulic bladder diaphragm rupture, loss of engine oil, damage to the engine, and loss of the airplane.
97-02-18: This amendment adopts a new airworthiness directive (AD), applicable to certain Jetstream Model BAe ATP airplanes, that requires repetitive inspections to detect damage of the antenna mounting reinforcing plates and surrounding fuselage skin. If any damage is detected, the AD requires replacement of the reinforcing plate with a new reinforcing plate and/or repair of the surrounding fuselage skin, which would terminate the repetitive inspection requirements. This amendment is prompted by reports of corrosion found at the antenna reinforcing plates, which was caused by the ingress of water at the plates. The actions specified by this AD are intended to prevent such corrosion, which could result in reduced structural integrity of the fuselage pressure vessel.
99-26-03: This amendment adopts a new airworthiness directive (AD) that is applicable to certain McDonnell Douglas Model MD-11 series airplanes. This action requires repetitive general visual inspections of the power feeder cables, terminal strip, fuseholder, and fuses of the galley load control unit (GLCU) within the No. 3 bay electrical power center to detect damage; and corrective actions, if necessary. This amendment is prompted by an incident of no power to the aft galleys and two incidents of sparking sounds coming from the G3 galley due to damage of the No. 3 and 4 wire assembly terminal lugs and overheating of the power feeder cables on the G3 GLCU. The actions specified in this AD are intended to prevent such damage due to the accumulated effects over time from overheating of the power feeder cables on the G3 GLCU, which could result in smoke and fire in the G3 galley.
2004-22-05: The FAA is adopting a new airworthiness directive (AD) for all Boeing Model 737-300, -400, and -500 series airplanes. This AD requires inspecting for discrepancies of the fuselage skin under the dorsal fin assembly, and repairing if necessary. This AD is prompted by a report of an 18-inch crack found in the fuselage skin area under the blade seals of the nose cap of the dorsal fin due to previous wear damage. We are issuing this AD to find and fix discrepancies of the fuselage skin, which could result in fatigue cracking due to cabin pressurization, and consequent rapid in-flight decompression of the airplane fuselage.
92-15-12: 92-15-12 AEROSPATIALE: Amendment 39-8306. Docket No. 92-NM-31-AD. Applicability: Model ATR42-300 and -320 series airplanes on which Modification 1694 (Aerospatiale Service Bulletin ATR42-32-0021) has been accomplished and on which Modification 2063 (Aerospatiale Service Bulletin ATR42-32-0028) has not been accomplished, certificated in any category. Compliance: Required as indicated, unless accomplished previously. To prevent a gear-up landing, accomplish the following: (a) Within 6 months after the effective date of this AD, modify the nose landing gear (NLG) retraction control logic, and perform a functional test of the landing gear retraction manual override control, in accordance with Aerospatiale Service Bulletin ATR42-32-0028, Revision 3, dated February 12, 1991. (b) An alternative method of compliance or adjustment of the compliance time that provides an acceptable level of safety may be used if approved by the Manager, Standardization Branch, ANM-113, FAA, Transport Airplane Directorate. Operators shall submit their requests through an appropriate FAA Principal Maintenance Inspector, who may add comments and then send it to the Manager, Standardization Branch. NOTE: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Standardization Branch. (c) Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate the airplane to a location where the requirements of this AD can be accomplished. (d) The modification and functional test shall be done in accordance with Aerospatiale Service Bulletin ATR42-32-0028, Revision 3, dated February 12, 1991, which includes the following list of effective pages: Page Number Revision Level Date 1-2, 11, 13-21 3 February 12, 1991 3-10, 12 1 February 23, 1990 This incorporation by reference was approved by the Director of the Federal Register in accordance with 5 U.S.C. 552(a) and 1 CFR Part 51. Copies may be obtained from Aerospatiale, 316 Route de Bayonne, 31060 Toulouse, Cedex 03, France. Copies may be inspected at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, Washington; or at the Office of the Federal Register, 1100 L Street NW., Room 8401, Washington, DC. (e) This amendment becomes effective on September 8, 1992.
2022-21-15: The FAA is adopting a new airworthiness directive (AD) for certain Diamond Aircraft Industries GmbH (DAI) Model DA 42, DA 42 NG, and DA 42 M-NG airplanes. This AD is prompted by mandatory continuing airworthiness information (MCAI) issued by the aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as a loose rudder T-yoke axle nut. This AD requires replacing the rudder T-yoke axle with an improved rudder T-yoke axle. The FAA is issuing this AD to address the unsafe condition on these products.
2022-21-02: The FAA is superseding Airworthiness Directive (AD) 2000-20- 15, which applied to certain Airbus SAS Model A300 and A300-600 series airplanes. AD 2000-20-15 required a high frequency eddy current (HFEC) inspection to detect cracking of the rear fittings of fuselage frame FR40 at stringer 27, and repetitive inspections or repair, as applicable. In lieu of accomplishing the repetitive inspections, AD 2000-20-15 provided a modification that would allow the inspection to be deferred for a certain period of time. This AD was prompted by cracking of the rear fittings of fuselage frame FR40 at stringer 27, and a determination that reduced compliance times are necessary. This AD removes airplanes from the applicability, and continues to require the actions in AD 2000-20-15, but at reduced compliance times, 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.
2004-22-01: This amendment adopts a new airworthiness directive (AD), applicable to various transport category airplanes on which cargo restraint strap assemblies have been installed per STC ST01004NY. This amendment requires revising the airplane flight manual to include a procedure for discontinuing the use of certain cargo restraint strap assemblies installed per STC ST01004NY, if used as the only cargo restraint. This amendment also requires revising the airplane weight and balance manual to include the same procedure described previously. The actions specified by this AD are intended to prevent shifting or unrestrained cargo in the cargo compartment, which could cause an unexpected change in the airplane's center of gravity, damage to the airplane structure and/or flight control system, a hazard to the flightcrew, and/or possible loss of controllability of the airplane. This action is intended to address the identified unsafe condition.
99-26-13: This amendment supersedes an existing airworthiness directive (AD), applicable to Agusta Model A109A and A109A II helicopters, that currently requires inspecting each tail rotor blade (blade) for a crack and replacing any cracked blade. This amendment requires, before further flight, inspecting any blade with 400 or more hours time-in-service (TIS) for a crack and replacing any cracked blade. This amendment is prompted by another report of a cracked blade since the issuance of the existing AD. Two of the three occurrences of cracked blades involved the loss of the tail rotor and 90-degree gearbox. The actions specified by this AD are intended to prevent fatigue failure of the blade, loss of the tail rotor, and subsequent loss of control of the helicopter.
2022-20-13: The FAA is adopting a new airworthiness directive (AD) for certain Airbus SAS Model A350-941 and A350-1041 airplanes. This AD was prompted by a determination that in the event of rapid decompression at a specific location of the airplane, possible deflections of the passenger floor cross beams may result in wiring damages, leading to potential system losses. This AD requires amending the operator's existing airplane flight manual (AFM) to update the landing performance database, 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.
91-06-14: 91-06-14 BRITISH AEROSPACE: Amendment 39-6936. Docket No. 90-NM-254-AD. Applicability: All Model ATP series airplanes, certificated in any category. Compliance: Required as indicated, unless previously accomplished. To detect disbonding of the nickel sheath from the propeller blades, accomplish the following: A. Within 125 hours time-in-service after the effective date of this AD, and thereafter at intervals not to exceed 125 hours time-in-service, perform a visual inspection of the propeller blades for disbonding of the leading edge nickel sheath, in accordance with British Aerospace Alert Service Bulletin A-ATP-61-5, dated April 4, 1990. B. If disbonding is found, prior to further flight, repair in a manner approved by the Manager, Standardization Branch, ANM-113, Transport Airplane Directorate. C. An alternate means of compliance or adjustment of the compliance time, which provides an acceptable level of safety, may be used when approved by the Manager, Standardization Branch, ANM-113, FAA, Transport Airplane Directorate. NOTE: The request should be submitted directly to the Manager, Standardization Branch, ANM-113, and a copy sent to the cognizant FAA Principal Inspector (PI). The PI will then forward comments or concurrence to the Manager, Standardization Branch, ANM-113. D. Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate airplanes to a base in order to comply with the requirements of this AD. All persons affected by this directive who have not already received the appropriate service documents from the manufacturer may obtain copies upon request to British Aerospace, PLC, Librarian for Service Bulletins, P.O. Box 17414, Dulles International Airport, Washington, D.C. 20041-0414. These documents may be examined at the FAA, Northwest Mountain Region, Transport Airplane Directorate, 1601 Lind Avenue S.W., Renton, Washington. This amendment (39-6936, AD 91-06-14) becomes effective on April 18, 1991.
99-26-10: This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 737-600, -700, and -800 series airplanes, that requires installation of a drain at each of the number 2 window frame assemblies in the airplane. This amendment is prompted by reports that flight deck emergency exits (number 2 windows) were found frozen shut after landing. The actions specified by this AD are intended to prevent water accumulation in the lower corners of the flight deck emergency exits (number 2 windows), which can freeze and prevent the exits from being used during an emergency evacuation.
2004-19-10: This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 737-100, -200, -200C, -300, -400, and -500 series airplanes, that requires repetitive inspections for corrosion and cracking of the pivot hinge pins of the horizontal stabilizer, certain follow-on inspections, and replacement of the hinge pins with new or serviceable pins if necessary. This action is necessary to prevent failure of the outer and inner hinge pins due to corrosion or cracking, which could allow the pins to migrate out of the joint and result in intermittent movement of the horizontal stabilizer structure and consequent loss of controllability of the airplane. This action is intended to address the identified unsafe condition.
2022-22-12: The FAA is adopting a new airworthiness directive (AD) for certain Bell Textron Inc., Model 204B, 205A, 205A-1, 205B, 210, 212, 412, 412CF, and 412EP helicopters; certain Erickson 214 Holdings, LLC, Model 214B and 214B-1 helicopters; certain Leonardo S.p.a. Model AB412 and AB412 EP helicopters; and certain various restricted category helicopters. This AD was prompted by reports of two in-service failures of forward crosstubes due to fatigue damage and the issuance of newly established life limits. This AD requires determining the total number of landings on certain part-numbered forward crosstubes and incorporating requirements (airworthiness limitations) into existing maintenance records. The FAA is issuing this AD to address the unsafe condition on these products.
77-09-04: 77-09-04 CANADAIR: Amendment 39-2885. Applies to Canadair CL-215-1A10 airplanes, Serial Nos. 1001 to 1040 inclusive, not altered with Canadair Reinforcement Kit K215- 30043 or an FAA approved equivalent. Compliance is required as indicated. To assure the structural integrity of the main landing gear wheel well angles, P/N 215- 32200-58, -59, -60, -61, accomplish the following: (a) On aircraft with 1000 or more hours in service, compliance with paragraph (c) is required before the next flight. The inspection of paragraph (c) must be repeated at intervals not to exceed 150 hours in service. (b) On aircraft with less than 1000 hours in service, compliance with paragraph (c) is required at or before 1000 hours in service. The inspections of paragraph (c) must be repeated at intervlas not to exceed 150 hours in service. (c) Inspect for cracks and modify in accordance with Canadair Service Information Circular No. 104-CL-215 dated September 5, 1975, or an equivalent approved by the Chief, Engineering and Manufacturing Branch, Eastern Region. (d) 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 compliance time in this AD. This amendment becomes effective May 9, 1977.
2022-20-15: The FAA is adopting a new airworthiness directive (AD) for all The Boeing Company Model 757 airplanes. This AD was prompted by a report of cracks found in the fastener holes at a certain location in the center wing box rear spar, lower skin. This AD requires repetitive inspections for cracking of certain areas of the center wing box rear spar, lower skin and lower chord; and repair. The FAA is issuing this AD to address the unsafe condition on these products.
2022-21-05: The FAA is adopting a new airworthiness directive (AD) for certain The Boeing Company Model 737-300, -400, and -500 series airplanes. This AD was prompted by a report that a spoiler sensor failure may go undetected by the autothrottle (A/T) computer. This AD requires repetitive built-in test equipment (BITE) tests of the A/T computer to detect a spoiler sensor failure, and corrective action if necessary. The FAA is issuing this AD to address the unsafe condition on these products.