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81-26-05 R1: 81-26-05 R1 FAIRCHILD AIRCRAFT CORP.: Amendment 39-4286 as amended by Amendment 39-5469. Applies to Models SA26T (S/N T26-2 through T26-99), and SA26-AT (S/N T26-100 through T26-999) airplanes certificated in any category. Compliance: Required within the next 25 hours time in service after the effective date of this AD, and thereafter at intervals not to exceed 200 hours time-in-service since last compliance, unless already accomplished. To prevent a failure at the lower forward wing station 99 attach joint, accomplish the following: (a) In accordance with Fairchild Service Bulletin 26-57-40-015, issued January 18, 1972, as revised June 26, 1986: (1) Remove the lower forward wing station 99 attach joint coverplate and wing attach bolt. (2) Inspect the lower forward wing station 99 attaching fitting for deterioration and cracks and, prior to further flight, replace damaged parts with new parts of the same part numbers. (3) Inspect the lower forwardwing station 99 attach bolt for identifying part number, deterioration and cracks and, prior to further flight, replace any damaged bolt or bolt not identified as P/N MS20014-29 bolt with a new P/N MS20014-29 bolt. (b) When the wing has been modified by (STC) SA1830NM, "Installation of Wing Spar Reinforcement," the inspection intervals required by this AD may be increased from 200 hours time-in-service to 1,500 hours time-in-service or every 3 years since last compliance, whichever occurs first. (c) The intervals between repetitive inspections required by this AD may be adjusted up to 10 percent of the specified interval to allow accomplishing these inspections concurrent with other scheduled maintenance of the airplane. (d) A special flight permit may be issued in accordance with FAR 21.197 to a location where this AD may be accomplished. (e) An equivalent method of compliance with this AD may be used when approved by the Manager, Airplane Certification Branch, ASW-150, Southwest Regional Office, FAA, Fort Worth, Texas 76101; Telephone (817) 624-5150. All persons affected by this AD may obtain copies of the documents referred to herein upon request to Fairchild Aircraft Corp., Post Office Box 32486, San Antonio, Texas 78284; and AviaDesign, Inc., Hangar 1, 173 Durley Avenue, Camarillo Airport, Camarillo, California 93010; or FAA, Office of the Regional Counsel, Room 1558, 601 East 12th Street, Kansas City, Missouri 64106. This AD revises AD 81-26-05, Amendment 39-4286, which became effective December 30, 1981. This amendment, 39-5469, becomes effective on December 29, 1986.
2010-17-17: We are adopting a new airworthiness directive (AD) for the products listed above. This AD results from mandatory continuing airworthiness information (MCAI) originated 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: There have been several Stick Pusher Capstan Shaft failures causing severe degradation of the stick pusher function. This directive is issued to revise the first flight of the day check of the stall protection system to detect degradation of the stick pusher function. It also introduces a new repetitive maintenance task to limit exposure to dormant failure of the stick pusher capstan shaft. Dormant loss or severe degradation of the stick pusher function could result in reduced controllability of the airplane. We are issuing this AD to require actions to correct the unsafe condition on these products.
2010-18-06: We are adopting a new airworthiness directive (AD) for the products listed above that will supersede an existing AD. This AD results from 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: Inspections have revealed cases of excessive wear in the forward slide of the cargo door. Excessive wear in the door slide may result in the door becoming detached from the aircraft in flight, with potentially catastrophic results. This AD requires actions that are intended to address the unsafe condition described in the MCAI.
86-15-04: 86-15-04 GENERAL ELECTRIC COMPANY: Amendment 39-5353. Applies to General Electric CF6- 80A/A1/A2/A3 turbofan engines. Compliance is required as indicated, unless already accomplished. To prevent cracking or uncontained failure of stage 1 high pressure turbine (HPT) disks, Part Numbers 9234M67 and 9367M45, inspect those serial number disks identified in, and in accordance with, General Electric CF6-80 Alert Service Bulletin (ASB) 72-446, dated June 1986, per the following schedule: (a) Disks that have been previously inspected at the forward side embossment per Service Bulletin (SB) 72-248, dated August 12, 1983, or FAA approved equivalent, must be inspected at the aft side embossment at the next HPT exposure, or prior to accumulating 5,300 service cycles since new, whichever occurs first. (b) Disks that have not been previously inspected at the forward side embossment per SB 72-248, dated August 12, 1983, or FAA approved equivalent, must be inspected at both the forward and aft side embossments at the next HPT exposure, or prior to accumulating 5,000 service cycles since new, whichever occurs first. (c) Remove from service, prior to further flight, any disk with a tool mark or crack indication. NOTE: Disks that have been previously inspected at both the forward and aft side embossments per CF6- 80A Series Engine Manual GEK72501, Section 72-53-02, are in compliance with the inspection requirement of ASB 72-446 and do not need to be reinspected. Aircraft may be ferried in accordance with the provisions of FAR 21.197 and 21.199 to a base where the AD can be accomplished. Upon request, an equivalent means of compliance with the requirements of this AD may be approved by the Manager, Engine Certification Office, Aircraft Certification Division, Federal Aviation Administration, New England Region, 12 New England Executive Park, Burlington, Massachusetts 01803. General Electric ASB 72-446, dated June 1986, identified and described in this document, is incorporated herein and made a part hereof pursuant to 5 U.S.C. 552(a)(1). All persons affected by this directive who have not already obtained this document from the manufacturer, may obtain copies upon request to General Electric Company, Director of Product Support, 111 Merchant Street, Cincinnati, Ohio 45246. This document may also be examined at the Office of the Regional Counsel, Federal Aviation Administration, 12 New England Executive Park, Burlington, Massachusetts 01803, Room 311, Rules Docket Number 86-ANE-23, between the hours of 8:00 a.m. and 4:30 p.m., Monday through Friday, except Federal holidays. This amendment, 39-5353, becomes effective on July 23, 1986.
83-07-17: 83-07-17 PARTENAVIA COSTRUZIONI AERONAUTICHE S.p.A: Amendment 39- 4619. Applies to Models P68B and P68C (from S/N 123 thru S/N 241) airplanes certificated in any category. Compliance: Required within the next 100 hours time-in-service after the effective date of this AD, unless already accomplished. To prevent failure of the stop tube for the fuel selector control system, accomplish the following: (a) Install stop tube kit (P/N 68-020) and adjust the fuel selector control receiver in accordance with Partenavia Costruzioni Aeronautiche S.p.A. Service Bulletin No. 52, dated March 20, 1981, and Service Instruction No. 13 dated March 24, 1981. (b) Conduct engine run to perform operational check of fuel selector control. Place fuel selector control handle in right tank position and then the left tank position to determine if fuel flow is restricted. (1) If fuel flow is not restricted, return airplane to service. (2) If fuel flow is restricted, readjustfuel selector in accordance with Partenavia Costruzioni Aeronautiche S.p.A Service Instruction No. 13 dated March 24, 1981, and repeat operational check of fuel selector control in accordance with paragraph (b) of this AD. (c) Aircraft may be flown in accordance with Federal Aviation Regulation 21.197 to a location where this AD can be accomplished. (d) An equivalent method of compliance with this AD, if used, must be approved by the Manager, Aircraft Certification Staff, AEU-100, Europe, Africa and Middle East Office, FAA, c/o American Embassy, 1000 Brussels, Belgium. This amendment becomes effective on April 14, 1983.
2010-18-04: We are adopting a new airworthiness directive (AD) for the products listed above. This AD results from mandatory continuing airworthiness information (MCAI) originated 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: It has been found the possibility of cracks developing in the ram air turbine (RAT) machined support, located in the forward compartment [zone 124] of [the] aircraft, due to downlock pin not [being] pull[ed] during its retraction. In case of RAT failure or malfunction, it will not provide electrical power to essential systems of [the] aircraft in [an] electrical emergency situation. * * * * * Lack of electrical power could result in reduced controllability of the airplane. We are issuing this AD to require actions to correct the unsafe condition on these products.
96-13-08: 96-13-08 PRATT & WHITNEY: Amendment 39-9676. Docket 96-ANE-10. Applicability: Pratt & Whitney (PW) PW4000 series turbofan engines, with thrust reverser, Supplemental Type Certificate (STC) No. SJ514NE, installed on Airbus A300-600 and A310 series aircraft, and thrust reverser, STC No. SE744NE, installed on McDonnell Douglas MD-11 series aircraft. These thrust reversers incorporate aft cascade support frame assemblies, Part Numbers (P/N's) 221-0516-503 and 221-0516-504. NOTE: This airworthiness directive (AD) applies to each engine with affected thrust reversers identified in the preceding applicability provision, regardless of whether it has been modified, altered, or repaired in the area subject to the requirements of this AD. For engines with affected thrust reversers that have been modified, altered, or repaired so that the performance of the requirements of this AD is affected, the owner/operator must use the authority provided in paragraph (c) to request approval from the Federal Aviation Administration (FAA). This approval may address either no action, if the current configuration eliminates the unsafe condition, or different actions necessary to address the unsafe condition described in this AD. Such a request should include an assessment of the effect of the changed configuration on the unsafe condition addressed by this AD. In no case does the presence of any modification, alteration, or repair remove any engine with affected thrust reversers from the applicability of this AD. Compliance: Required as indicated, unless accomplished previously. To prevent aft cascade support frame assembly failure due to cracks, which can result in thrust reverser hardware liberation and ejection from the aircraft during thrust reverser operation, which can contaminate the runway with debris, causing an operational hazard to other aircraft during takeoff and landing, accomplish the following: (a) For engines with affected thrust reversers installed on Airbus A300-600 and A310 series aircraft, accomplish the following: (1) Initially inspect aft cascade support frame assemblies for cracks within 250 flight hours after the effective date of this AD, in accordance with the Accomplishment Instructions, Part 1 -- Interim Inspection, of PW Service Bulletin (SB) No. PW4NAC 78-78, Revision 6, dated March 6, 1996. (2) Thereafter, inspect aft cascade support frame assemblies for cracks at intervals not to exceed 450 flight hours since the last inspection, in accordance with the Accomplishment Instructions, Part 1 -- Interim Inspection, of PW SB No. PW4NAC 78-78, Revision 6, dated March 6, 1996. (3) For aft cascade support frame assemblies that do not meet the return to service criteria stated in the Accomplishment Instructions, Part 1 -- Interim Inspection, of PW SB No. PW4NAC 78-78, Revision 6, dated March 6, 1996, prior to further flight, accomplish either of the following: (i) Remove from service cracked aft cascade support frame assemblies, and replace with a serviceable part; or (ii) Lockout the thrust reverser in accordance with the Airbus A300- 600 and A310 series Aircraft Maintenance Manuals, as applicable, for a time period not to exceed 10 days. At the conclusion of the 10-day lockout period, prior to further flight remove any cracked aft cascade support frame assemblies and replace with serviceable parts. (b) For engines with affected thrust reversers installed on McDonnell Douglas MD- 11 series aircraft, accomplish the following: (1) Initially inspect aft cascade support frame assemblies for cracks within 250 flight hours after the effective date of this AD, in accordance with the Accomplishment Instructions, Part 1 -- Interim Inspection, of PW SB No. PW4MD11 78-67, Revision 5, dated March 6, 1996. (2) Thereafter, inspect aft cascade support frame assemblies for cracks at intervals not to exceed 450 flight hours since the last inspection, in accordance with the Accomplishment Instructions, Part 1 -- Interim Inspection, of PW SB No. PW4MD11 78-67, Revision 5, dated March 6, 1996. (3) For aft cascade support frame assemblies that do not meet the return to service criteria stated in the Accomplishment Instructions, Part 1 -- Interim Inspection, of PW SB No. PW4MD11 78-67, Revision 5, dated March 6, 1996, prior to further flight, accomplish either of the following: (i) Remove from service cracked aft cascade support frame assemblies, and replace with a serviceable part; or (ii) Lockout the thrust reverser in accordance with the McDonnell Douglas MD-11 series Aircraft Maintenance Manual, for a time period not to exceed 10 days. At the conclusion of the 10-day lockout period, prior to further flight remove any cracked aft cascade support frame assemblies and replace with serviceable parts. (c) 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, Engine Certification Office. The request should be forwarded through an appropriate FAA Principal Maintenance Inspector, who may add comments and then send it to the Manager, Engine Certification Office. NOTE: Information concerning the existence of approved alternative methods of compliance with this airworthiness directive, if any, may be obtained from the Engine Certification Office. (d) Special flight permits may be issued in accordance with sections 21.197 and 21.199 of the Federal Aviation Regulations (14 CFR 21.197 and 21.199) to operate the aircraft to a location where the requirements of this AD can be accomplished. (e) The actions required by this AD shall be done in accordance with the following PW SB's: Document No. Pages Revision Date PW4NAC 78-78 1 6 March 6, 1996 2,3 2 October 31, 1995 4-6 6 March 6, 1996 7 5 October 31, 1995 8-11 6 March 6, 1996 12 5 October 31, 1995 13-19 6 March 6, 1996 20-22 5 October 31, 1995 23-34 6 March 6, 1996 35 5 October 31, 1995 36,37 6 March 6, 1996 38 5 October 31, 1995 39,40 6 March 6, 1996 Total pages: 40. PW4MD11 78-67 1-38 5 March 6, 1996 Total pages: 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 Pratt & Whitney, 400 Main St., East Hartford, CT 06108; telephone (860) 565-6600, fax (860) 565-4503. Copies may be inspected at the FAA, New England Region, Office of the Assistant Chief Counsel, 12 New England Executive Park, Burlington, MA; or at the Office of the Federal Register, 800 North Capitol Street, NW., suite 700, Washington, DC. (f) This amendment becomes effective on August 1, 1996.
2010-17-15: We are adopting a new airworthiness directive (AD) for certain Hawker Beechcraft Corporation Model 390 airplanes. This AD requires you to inspect for installation of certain serial number (S/N) starter generators and replace the starter generator if one with an affected serial number is found. This AD results from reports that starter generators with deficient armature insulating materials may have been installed on certain airplanes. We are issuing this AD to detect and replace starter generators with defective armature insulating materials. This condition could result in the loss of operation of one or both starter generators with consequent loss of all non battery electrical power.
75-26-10: 75-26-10 SIKORSKY AIRCRAFT: Amendment 39-2461. Applies to S-61L, S-61N, and S-61NM helicopters certificated in all categories. Compliance required as indicated. As a result of the completion of a recent engineering evaluation program and the development of additional substantiating data, a new schedule of replacement times has been established for the components of S-61 helicopters. (a) After the effective date of this AD, the replacement of S-61 components must be accomplished in accordance with the schedule of Section 2C of Sikorsky Service Bulletin No. 61B General-1F dated October 20, 1975, or later FAA approved revisions. (b) 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. 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 Sikorsky Aircraft, Stratford, Connecticut 06602. These documents may also be examined at FAA, New England Region, 12 New England Executive Park, Burlington, Massachusetts 01803, and at FAA Headquarters, 800 Independence Avenue, S.W., Washington, D.C. 20591. 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, New England Region, Burlington, Massachusetts. This supersedes Amendment 39-1167 (36 F.R. 4689), AD 71-06-02 as amended by Amendment 39-1271 (36 F.R. 16186), Amendment 39-1948 (39 F. R. 31626), and Amendment 39-1978 (39 F.R. 34649). This amendment becomes effective January 2, 1976.
94-13-08: This amendment adopts a new airworthiness directive (AD) that is applicable to certain Airbus Model A310 and A300-600 series airplanes. This action requires inspections and replacement or reinstallation of certain aft engine mount link assemblies. This amendment is prompted by reports of cracking in the aft engine mount link assemblies. The actions specified in this AD are intended to prevent loss of the capability of the aft engine mount to support engine loads, and possible separation of the engine from the airplane.