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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.