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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.