Results
2022-17-05: The FAA is superseding Airworthiness Directive (AD) 2002-14- 28, which applied to all de Havilland Inc. (type certificate currently held by Viking Air Limited) Model DHC-2 Mk. I, DHC-2 Mk. II, and DHC-2 Mk. III airplanes. AD 2002-14-28 established a life limit for the front fuselage struts and required repetitively replacing the front fuselage struts every 15 years or repetitively inspecting the struts for corrosion or fatigue damage and replacing when the damage exceeded a certain level. Since the FAA issued AD 2002-14-28, Transport Canada superseded its mandatory continuing airworthiness information (MCAI) to correct this unsafe condition on these products. This AD requires either doing recurring visual inspections, borescope inspections, and non-destructive inspections (NDIs) of the struts and airframe lugs with corrective action as necessary or replacing the struts every 15 years and doing recurring NDIs of the airframe lugs with corrective action as necessary. The FAA is issuing this AD to address the unsafe condition on these products.
2014-05-30: We are superseding Airworthiness Directive (AD) 2013-07-07 for all The Boeing Company Model 737-600, -700, -700C, -800, -900, and - 900ER series airplanes. AD 2013-07-07 required inspecting to determine the part number of the attach pins of the horizontal stabilizer rear spar, and replacing certain attach pins. This new AD clarifies the parts installation limitation and prohibition, and adds a new requirement for certain airplanes on which certain attach pins were installed. This AD was prompted by inquiries from affected operators regarding the parts installation limitation and prohibition, and re- installation of certain attach pins that were removed for inspection. We are issuing this AD to prevent premature failure of the attach pins, which could cause reduced structural integrity of the horizontal stabilizer to fuselage attachment, resulting in loss of control of the airplane.
99-21-33: This amendment adopts a new airworthiness directive (AD), applicable to certain Fokker Model F.27 Mark 050 series airplanes. This action requires a one-time inspection to detect improper installation of countersunk screws used to attach the access panels to the bottom skin of the center wing; and corrective action, if necessary. This amendment is prompted by issuance of mandatory continuing airworthiness information by a foreign civil airworthiness authority. The actions specified in this AD are intended to detect and correct such improper installation, which could result in fatigue cracking of the bottom skin of the center wing and consequent reduced structural integrity of the airplane.
92-14-10: 92-14-10 DE HAVILLAND, INC.: Amendment 39-8292. Docket No. 92-NM-32-AD. Supersedes AD 83-07-25, Amendment 39-4631. Applicability: Model DHC-7 series airplanes; as listed in de Havilland Service Bulletin 7-27-46, Revision B, dated December 17, 1982, certificated in any category. Compliance: Required as indicated, unless accomplished previously. To prevent inadvertent deployment of the ground spoilers and loss of lift, accomplish the following: (a) Within 15 hours time-in-service or 7 days after April 25, 1983 (the effective date of AD 83-07-25, Amendment 39-4631), whichever occurs first, perform a functional check of the ground spoiler control system, in accordance with the Accomplishment Instructions of de Havilland Alert Service Bulletin 7-27-46, Revision A, dated November 19, 1982; or de Havilland Service Bulletin 7-27-46, Revision B, dated December 17, 1982. (b) If the check required by paragraph (a) of this AD shows incorrect indications, operate theairplane in accordance with the Airplane Flight Manual Minimum Equipment List Supplement No. 4 until the requirements of paragraph (d) of this AD are accomplished. (c) Repeat the functional checks required by paragraph (a) of this AD at intervals not to exceed 15 hours time-in-service, or 7 days, whichever occurs first. (d) Within 6 months after the effective date of this AD, accomplish either paragraph (d)(1) or (d)(2) of this AD, as applicable, in accordance with de Havilland Service Bulletin 7-27- 46, Revision B, dated December 17, 1982: (1) For airplanes having serial numbers 1 through 73, inclusive, that have been retrofitted with Modification No. 7/1732; and airplanes having serial numbers 74 through 83, inclusive, 85, 86, and 89: Incorporate Modification No. 7/2296, in accordance with the service bulletin. (2) For airplanes having serial numbers 1 through 73, inclusive, that have not been retrofitted with Modification No. 7/1732; and airplanes having serial numbers 84, 87, 88, and 90 through 93, inclusive: Incorporate Modification No. 7/2294, in accordance with the service bulletin. (e) Incorporation of Modification No. 7/2296 or 7/2294, as required by paragraph (d)(1) or (d)(2) of this AD, constitutes terminating action for the repetitive functional checks required by paragraph (c) of this AD. (f) 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, New York Aircraft Certification Office (ACO), ANE-170, FAA, Engine and Propeller Directorate. Operators shall submit their requests through an FAA Principal Maintenance Inspector, who may concur or comment and then send it to the Manager, New York ACO. NOTE: Information concerning the existence of approved alternative methods of compliance with this airworthiness directive, if any, may be obtained from the New York ACO. (g) Special flight permits may be issuedin accordance with FAR 21.197 and 21.199 to operate the airplane to a location where the requirements of this AD can be accomplished. (h) The functional checks and modifications shall be done in accordance with de Havilland Service Bulletin 7-27-46, Revision A, dated November 19, 1982; and de Havilland Service Bulletin 7-27-46, Revision B, dated December 17, 1982, which contains the following list of effective pages: Page Number Revision Level Date 1-4 B December 17, 1982 5-7 A November 19, 1982 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 de Havilland, Inc., Garratt Boulevard, Downsview, Ontario M3K 1Y5, Canada. Copies may be inspected at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, Washington; or at the FAA, New England Region, New York Aircraft Certification Office, 181 South Franklin Avenue, Room 202, ValleyStream, New York; or at the Office of the Federal Register, 1100 L Street NW., Room 8401, Washington, DC. (i) This amendment becomes effective on August 20, 1992.
93-13-08: 93-13-08 AEROSTAR AIRCRAFT CORPORATION: Amendment 39-8621. Docket No. 92-CE-51-AD. Supersedes AD 92-11-08, Amendment 39-8258 which superseded AD 80-02-09, Amendments 39-3665 and 39-3991. Applicability: The following model and serial number airplanes, certificated in any category: Models Serial Numbers PA-60-600 Aerostar 600 60-0001-003 through 60-0933-8161262 PA-60-601 Aerostar 601 61-0001-004 through 61-0880-8162157 PA-60-601P Aerostar 601P 61P-0157-001 through 61P-0860-8163455 PA-60-602P Aerostar 602P 62P-0750-8165001 through 60-8365021 PA-60-700P Aerostar 700P 60-8223001 through 60-8423025 NOTE 1: The manufacturing and ownership rights of the affected model airplanes were previously owned by the Piper Aircraft Corporation, but these rights were recently transferred to the Aerostar Aircraft Corporation. Compliance: Required as indicated, unless already accomplished. To prevent loss of directional control of the airplane during ground operation caused by torque link failure, accomplish the following: (a) Within the next 100 hours time-in-service (TIS) after the effective date of this AD, accomplish either (1) or (2) below: (1) Replace the existing main landing gear torque links with improved design torque links, part number (P/N) 400126-501 and 400126-503 (left main landing gear) and P/N 400126-502 and 400126-504 (right main landing gear), in accordance with the INSTRUCTIONS section of Aerostar Service Bulletin (SB) No. 746C, dated September 15, 1992. NOTE 2: Aerostar SB No. 746C, dated September 15, 1992, references the availability of Main Landing Gear Torque Link Replacement Kit No. 765-155 revision G. This kit contains the improved torque links and all hardware necessary to install these links. This kit may be obtained from the manufacturer at the address specified in paragraph (d) of this AD. (2) Dye penetrant inspect (using FAA-approved methods) the main landing gear torque links for cracks. (i) If cracks are found, prior to further flight, replace the cracked torque links with improved designed torque links part number (P/N) 400126-501 and 400126-503 (left main landing gear) and P/N 400126-502 and 400126-504 (right main landing gear), in accordance with the INSTRUCTIONS section of Aerostar SB No. 746C, dated September 15, 1992. (ii) If no cracks are found, reinspect at intervals not to exceed 100 hours TIS. (iii) The repetitive inspection requirement is no longer required when both the left and right main landing gear torque links are replaced with improved design torque links, part number (P/N) 400126-501 and 400126-503 (left main landing gear) and P/N 400126-502 and 400126-504 (right main landing gear), in accordance with the INSTRUCTIONS section of Aerostar SB No. 746C, dated September 15, 1992. This installation may be accomplished at any time regardless of whether cracks are found during the inspection. NOTE 3: Operators should ensure that proper strut inflation is maintained as improper strut inflation could put extreme impact upon the torque links. In addition, improper use of the hydraulic nose gear steering mechanism at high speeds could also lead to overstressed torque links. (b) 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. (c) An alternative method of compliance or adjustment of the compliance time that provides an equivalent level of safety may be approved by the Manager, Seattle Aircraft Certification Office, 1601 Lind Avenue, S.W., Renton, Washington 98055-4056. The request shall be forwarded through an appropriate FAA Maintenance Inspector, who may add comments and then send it to the Manager, Seattle Aircraft Certification Office. NOTE 4: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained fromthe Seattle Aircraft Certification Office. (d) The replacement required by this AD shall be done in accordance with Aerostar Service Bulletin No. 746C, dated September 15, 1992. 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 the Aerostar Aircraft Corporation, Customer Service Department, South 3608 Davison Boulevard, Spokane, Washington 99204. Copies may be inspected at the FAA, Central Region, Office of the Assistant Chief Counsel, Room 1558, 601 E. 12th Street, Kansas City, Missouri, or at the Office of the Federal Register, 800 North Capitol Street, NW., suite 700, Washington, DC. (e) This amendment (39-8621) supersedes AD 92-11-08, Amendment 39-8258 which superseded AD 80-02-09, Amendments 39-3665 and 39-3991. (f) This amendment becomes effective on August 20, 1993.
2022-17-01: The FAA is adopting a new airworthiness directive (AD) for certain Airbus Helicopters Deutschland GmbH (AHD) Model EC135P1, EC135P2, EC135P2+, EC135P3, EC135T1, EC135T2, EC135T2+, and EC135T3 helicopters. This AD was prompted by reports of the air conditioning system (ACS) malfunctioning. This AD requires deactivating the ACS and prohibits installing the affected parts, 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.
2014-05-20: We are adopting a new airworthiness directive (AD) for all The Boeing Company Model 757 airplanes. This AD was prompted by reports of fractured rudder pedal pushrod connecting bolts in a rudder pedal assembly. This AD requires repetitive replacements of the rudder pedal pushrod connecting bolts and repetitive inspections of the rudder pedal assembly bolt holes in each of the captain and the first officer rudder pedal assemblies, and if necessary, repair or replacement of worn rudder pedal assemblies. We are issuing this AD to prevent fracture of the rudder pedal pushrod connecting bolts during pedal use, which could result in large involuntary inputs to the rudder and nose-wheel steering and an asymmetric application of braking, if pedal brakes are applied, leading to a runway excursion.
99-21-31: This amendment adopts a new airworthiness directive (AD), applicable to certain Saab Model SAAB SF340A and SAAB 340B series airplanes, that requires removing the control quadrant, securing the power lever cam screws with Loctite, and reinstalling the control quadrant. 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 the cam screws of the engine power levers from backing out and interfering with the movement of the engine power levers, which could result in limited engine power, and consequent reduced controllability of the airplane.
61-16-04: 61-16-04 BRANTLY: Amdt. 319 Part 507 Federal Register August 4, 1961. Applies to Model B-2 Helicopters as indicated. Compliance required within the next 25 hours' time in service after the effective date of this directive. Failures of the right forward mount lug of the upper transmission case have occurred on three Brantly B-2 helicopters. These failures are fatigue in nature and apparently are associated with an undesirable pre-stress in the mount lug introduced during assembly procedures. Since this condition is likely to exist in other such aircraft, it is necessary to require the following modifications: (a) Applies to all Model B-2 helicopters prior to Serial Number 56 except Serial Numbers 16, 31, 44, 51, 52, and 53. (1) Remove the main rotor and transmission and the three vertical control rods which protrude through the steel plate at the top of the forward firewall. (2) Rework the upper surface of the left and right forward transmission mountpads as follows: Insert a 5/16-inch diameter bolt downward through an AN 960-516 washer into the transmission mount bolt hole. File approximately 0.015 inch from the top surface of the mount pad except where protected by the washer. Remove bolt and washer. (3) Rework the lower surface of the left and right forward transmission mount pads as follows: Enlarge the lower 1/4 inch of the 5/16-inch diameter transmission mount bolt hole by drilling upward with a 21/64-inch drill. Use of a drill stop is strongly recommended to avoid exceeding the 1/4-inch depth of this rework. (4) Apply zinc chromate finish to reworked areas and reinstall transmission, rotor assembly, and control rods in accordance with Brantly Maintenance Manual procedures. (Brantly Service Bulletin No. 9 covers this same subject.) (b) Applies to all Model B-2 helicopters prior to Serial Number 103 except those with 0.375-inch thick mount lugs on P/N B2-104-2 upper transmission case. (1) Remove the NAS 145-22 bolt through the right forward transmission mount lug and the two AN 3-24A bolts through the upper transmission case (P/N B2-104-2) immediately inboard of the mount lug. (2) Install transmission bracket P/N B2-151-19 on top of the right forward transmission case mount lug and attach with new bolts and nuts through mating holes in transmission case previously exposed by (b) (1). These parts are furnished by Brantly Helicopter Corporation as their Modification Kit No. 20. (3) Insure a close fit of faying surfaces between the upper transmission case and bracket P/N B2-151-19 by accomplishing the following steps: Break sharp edges of the upper transmission case ledge to avoid interference with the inner radii of the new bracket; remove material from the upper transmission case ledge or from the lower surface of the bracket in contact with the case lug, as necessary. Failure to insure proper fit of this bracket will introduce undesirable pre-stress into thetransmission mount lug. (Brantly Service Bulletin No. 14 covers this same subject.) This directive effective August 14, 1961.
92-11-04: 92-11-04 BRITISH AEROSPACE: Amendment 39-8254. Docket No. 91-NM-166-AD. Applicability: British Aerospace Model ATP airplanes; as listed in British Aerospace Service Bulletin ATP-24-34, dated April 25, 1991, and British Aerospace Service Bulletin ATP-33-8, Revision 2, dated April 11, 1991; certificated in any category. Compliance: Required as indicated, unless accomplished previously. To prevent inaccurate navigation when using the standby compass, accomplish the following: (a) Within 14 days after the effective date of this AD, fabricate and install a temporary placard near the standby magnetic compass, worded as follows: "WARNING: OPERATION OF CABIN ROOF AND SIDEWALL LIGHTING, PITOT HEAT, AND STALL WARNING SYSTEMS MAY INDUCE EXCESSIVE ERROR IN THE MAGNETIC COMPASS READINGS." (b) Within 8 months after the effective date of this AD, accomplish the following: (1) Modify the earthing arrangements to the pitot static and stall warning systems (Modification 10194A) and to the overhead stowage units (Modification 10194B), as applicable, in accordance with British Aerospace Service Bulletin ATP 24-34, dated April 25, 1991. (2) Modify the roof and sidewall light wiring (Modification 35113A) in accordance with British Aerospace Service Bulletin ATP-33-8, Revision 2, dated April 11, 1991. (3) Accomplish a compass swing of the standby compass in accordance with British Aerospace Service Bulletin ATP-24-34, dated April 25, 1991. (4) Remove the temporary placard installed in accordance with paragraph (a) of this AD. (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, Standardization Branch, ANM-113, FAA, Transport Airplane Directorate. The request shall be forwarded through an FAA Principal Maintenance Inspector, who may concur or comment and then send it 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 the airplane to a location where the requirements of this AD can be accomplished. (e) The modifications shall be done in accordance with British Aerospace Service Bulletin ATP-24-34, dated April 25, 1991; and British Aerospace Service Bulletin ATP-33-8, Revision 2, dated April 11, 1991. These service bulletins contain the following list of effective pages: Service Bulletin No. Page Number Revision Level Date ATP-24-34 1-3, 5-21, Original April 25, 1991 23, 25, 27, 29, 31, 33, 35, 37, 39, 41, 43, 45, 47, 49, 51, 53-54 4, 22, 24, (These pages are not used) 26, 28, 30, 32, 34, 36, 38, 40, 42, 44, 46, 48, 50, 52 ATP-33-8 1 2 April 11, 1991 Revision 2 2-5, 19-20, 1 September 5, 1990 31, 33 6-18, 21, 23, Original April 29, 1990 25, 27,29, 35, 37, 39-40 22, 24, 26, (These pages are not used) 28, 30, 32, 34, 36, 38 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 British Aerospace, PLC, Librarian for Service Bulletins, P.O. Box 17414, Dulles International Airport, Washington, D.C. 20041-0414. 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. (f) This amendment becomes effective on July 23, 1992.