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89-26-09: 89-26-09 BRITISH AEROSPACE: Amendment 39-6420. Docket No. 88-NM-169-AD. Applicability: British Aerospace (BAe) Model 146-100A, -200A and -300A series airplanes, certificated in any category. Compliance: Required as indicated, unless previously accomplished. To prevent loss of roll control should a jam in aileron control system occur, accomplish the following: A. Within 60 days after the effective date of this AD: 1. Determine if Fraser Nash Part Number AO-100-902 aileron disconnect units (ADU's) or Normalair-Garrett, Ltd. (NGL) Part Numbers 1099R000, 1224R000, or 1295R000 ADU's are installed. If NGL Part Number 1295R000 ADU's modified to British Aerospace (BAe) Modification HCM70212C (NGL Modification No. 5RM) configuration are installed, no further action is required. 2. Modify NGL Part Number 1295R000 ADU's to BAe modification HCM70212C (NGL modification 5RM) configuration, in accordance with BAe Modification Service Bulletin 27-88-70212C, dated November 10, 1988. 3. Inspect Fraser Nash Part Number AO-100-902 and NGL Part Numbers 1099R000 and 1224R000 ADU's for dormant failure, in accordance with British Aerospace Inspection Service Bulletin 27-87, dated September 30, 1988. Replace any failed units with serviceable units prior to further flight. B. For all airplanes equipped with NGL Part Numbers 1099R000 and 1224R000 ADU's that have not been previously modified to BAe HCM 70212A&B (NGL Modification 3RM and 4RM) configuration: 1. Within one year after the effective date of this AD, modify NGL Part Number 1099R000 and 1224R000 ADU's to BAe HCM70212A&B (NGL Modification 3RM and 4RM) and BAe HCM70212C (NGL Modification 5RM) configuration, in accordance with BAe Modification Service Bulletins 27-75-70212A&B, dated June 16, 1988, and 27-88-70212C, dated November 10, 1988. NOTE: British Aerospace Modification Service Bulletin 27-75-70212A&B refers to NGL Service Bulletins 1099R-27-4 and 1224R-27-5. British Aerospace Modification Service Bulletin 27-88-70212C refers to NGL Service Bulletin 1295R-27-6, Revision 1, and NGL Service News Letter, dated September 12, 1988, for specific installation procedures. 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, Northwest Mountain Region. NOTE: The request should be forwarded through an FAA Principal Maintenance Inspector (PMI), who will either 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 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, Librarian for Service Bulletins, P.O. Box 17414, Dulles International Airport, Washington, D.C. 20041. These documents may be examined at the FAA, Northwest Mountain Region, Transport Airplane Directorate, 17900 Pacific Highway South, Seattle, Washington, or the Standardization Branch, 9010 East Marginal Way South, Seattle, Washington. This amendment (39-6420, AD 89-26-09) becomes effective on January 14, 1990.
93-05-08: 93-05-08 BOEING: Amendment 39-8513. Docket 92-NM-146-AD. \n\n\tApplicability: Model 757 series airplanes, as listed in Boeing Alert Service Bulletin 757- 26A0028, Revision 1, dated April 23, 1992; and Model 767 series airplanes, as listed in Boeing Alert Service Bulletin 767-26A0081, dated February 13, 1992; certificated in any category. \n\n\tCompliance: Required as indicated, unless accomplished previously.\n \n\tTo prevent reduced sensitivity of the smoke detector, accomplish the following: \n\n\t(a)\tWithin 24 months after the effective date of this AD, examine the smoke detectors in the cargo compartment and equipment cooling systems to determine if the correct caution decal is installed, in accordance with Autronics Service Bulletin 2156204A-26-02, dated January 17, 1992. \n\n\t\t(1)\tIf the caution decal is incorrect, prior to further flight, apply a correct caution decal over the existing decal and inspect the lamp inside the smoke detector to determine its part number, in accordance with the Autronics Service Bulletin. \n\n\t\t(2)\tIf an incorrect lamp is installed, prior to further flight, replace it with one having the correct part number, in accordance with the Autronics Service Bulletin. \n\n\tNOTE: Boeing Alert Service Bulletin 757-26A0028, Revision 1, dated April 23, 1992; and Boeing Alert Service Bulletin 767-26A0081, dated February 13, 1992; describe procedures for gaining access to the smoke detectors in the cargo compartment and equipment cooling systems. \n\n\t(b)\tIf it is necessary to remove any smoke detector during the inspection required by paragraph (a) of this AD, immediately after reinstalling the smoke detector, perform a functional test in accordance with Boeing Alert Service Bulletin 757-26A0028, Revision 1, dated April 23, 1992; or Boeing Alert Service Bulletin 767-26A0081, dated February 13, 1992; as applicable. \n\n\t(c)\tReplacement of a smoke detector with a smoke detector that has been inspected previously in accordance with Autronics Service Bulletin 2156204A-26-02, dated January 17, 1992, constitutes terminating action for the requirements of paragraph (a) of this AD, for that smoke detector. However, the functional test required by paragraph (b) of this AD must be accomplished. \n\n\t(d)\tAn 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, Seattle Aircraft Certification Office (ACO). Operators shall submit their requests through an appropriate FAA Principal Maintenance Inspector, who may add comments and then send it to the Manager, Seattle ACO. \n\n\tNOTE: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Seattle ACO. \n\n\t(e)\tSpecial 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. \n\n\t(f)\tThe inspection and replacementrequirements shall be done in accordance with Autronics Service Bulletin 2156204A-26-02, dated January 17, 1992. The functional test shall be done in accordance with Boeing Alert Service Bulletin 757-26A0028, Revision 1, dated April 23, 1992; or Boeing Alert Service Bulletin 767-26A0081, dated February 13, 1992; as applicable. 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 Boeing Commercial Airplane Group, P.O. Box 3707, Seattle, Washington 98124; or from Autronics Corporation, 314 East Live Oak Avenue, Arcadia, California 91006-5617. Copies may be inspected at the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington; or at the Office of the Federal Register, 800 North Capitol Street, NW., suite 700, Washington, DC. \n\n\t(g)\tThis amendment becomes effective on April 29, 1993.
89-21-03: 89-21-03 BOEING: Amendment 39-6347. Docket No. 89-NM-176-AD. \n\tApplicability: Model 747 series airplanes equipped with a Door 5 crew rest area, certificated in any category. \n\n\tCompliance: Required within the next 60 days after the effective date of this AD, unless previously accomplished.\n \n\tTo ensure proper operation of the oxygen generators, accomplish the following: \n\n\tA.\tReplace the oxygen generator release cable assembly in accordance with Boeing Alert Service Bulletin 747-35A2065, dated August 3, 1989. \n\n\tB.\tAn 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, Seattle Aircraft Certification Office, FAA, Northwest Mountain Region. \n\n\tNOTE: The request should be forwarded through an FAA Principal Maintenance Inspector (PMI), who will either concur or comment, and then send it to the Manager, Seattle Aircraft Certification Office. \n\n\tC.\tSpecial 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. \n\n\tAll persons affected by this directive who have not already received the appropriate service documents from the manufacturer may obtain copies upon request to Boeing Commercial Airplanes, P.O. Box 3707, Seattle, Washington 98124. These documents may be examined at the FAA, Northwest Mountain Region, Transport Airplane Directorate, 17900 Pacific Highway South, Seattle, Washington, or Seattle Aircraft Certification Office, 9010 East Marginal Way South, Seattle, Washington. \n\n\tThis amendment (39-6347, AD 89-21-03) becomes effective on October 19, 1989.
91-16-06: 91-16-06 FOKKER: Amendment 39-7096. Docket No. 91-NM-83-AD. Applicability: Model F-28 Mark 0100 series airplanes; Serial Numbers 11244 through 11264, 11268 through 11283, 11286, 11289, 11291, 11293, 11295, and 11297; certificated in any category. Compliance: Required within one year after the effective date of this AD, unless previously accomplished. To prevent loss of communications and reduced capability to comply with air traffic control separation procedures, accomplish the following: A. Remove all audio control panels and replace with modified audio control panels, in accordance with Fokker Service Bulletin F100-23-014, dated November 7, 1990. NOTE: The Fokker service bulletin references Gables Service Bulletins G6937XX SB#2, Revision 1, dated March 1, 1991; G6939-12 SB#3, dated February 6, 1990; and G6968-02 SB#2, dated February 6, 1990; for additional instructions. 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 Avionics 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. D. The replacement requirement shall be done in accordance with Fokker Service Bulletin F100-23-014, dated November 7, 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 Fokker Aircraft USA, Inc., 1199 North Fairfax Street, Alexandria, Virginia 22314. Copies may be inspected at the FAA, Transport Airplane Directorate, Renton, Washington; or at the Office of the Federal Register, 1100 L Street N.W., Room 8401 Washington, D.C. This amendment (39-7096, AD 91-16-06) becomes effective on September 11, 1991.
97-04-07: This amendment supersedes an existing airworthiness directive (AD), applicable to certain Airbus Model A300-600 and A310 series airplanes, that currently requires repetitive visual inspections and tap tests of the rudder skin panels to detect disbonding; and repairs, if necessary. That AD was prompted by reports of weakening of the bonding material between the core of the rudder and its inner and outer skin, and cracking of the core. This amendment adds repetitive elasticity laminate checker (ELCH) inspections of the rudder in place of the currently required tap tests. It also requires replacement of the rudder with a modified rudder, which will terminate the repetitive inspections. The actions specified by this AD are intended to detect and prevent disbonding of the rudder, which, if not corrected, could reduce the structural integrity of the rudder, and consequently lead to a reduction in its ability to sustain limit loads.
90-20-02: 90-20-02 BOEING: Amendment 39-6739. Docket No. 90-NM-48-AD. \n\n\tApplicability: Model 727 series airplanes, listed in Boeing Service Bulletin 727-57-0107, Revision 6, dated November 22, 1989, certificated in any category. \n\n\tCompliance: Required as indicated, unless previously accomplished. \n\n\tTo detect cracks in the wing center section front spar web, accomplish the following: \n\n\tA.\tExcept as provided in paragraphs F. and G. of this AD, prior to the accumulation of 15,000 landings since manufacture, or prior to the accumulation of 500 additional landings after September 11, 1986 (the effective date of AD 86-18-03, Amendment 39-5384), whichever occurs later, visually inspect the wing center section for cracks in accordance with Figure 1 of Boeing Service Bulletin 727-57-107, Revision 6, dated November 22, 1989 (hereafter referred to as "the service bulletin"). If no cracks are detected, repeat the visual inspection at intervals not to exceed 1,000 landings. \n\n\tB.\tIf a single crack less than two inches in length is detected on either side of body buttock line (BBL) 0.0, before further flight, the crack must be stop-drilled at each end in accordance with the Boeing 727 Structural Repair Manual (SRM), and visually reinspected at intervals not to exceed 10 landings for crack growth beyond the stop holes. If crack growth occurs beyond any stop hole, accomplish the procedures required by paragraph C. or D. of this AD. \n\n\tC.\tIf a single crack between two and five inches in length is detected on either side of BBL 0.0, before further flight, the crack must be stop-drilled at each end in accordance with the Boeing 727 SRM, and the crack must be repaired in accordance with Boeing Drawing Number 69-62491-2. Visually reinspect the affected area at intervals not to exceed 200 landings for crack growth beyond any stop hole. If crack growth occurs beyond any stop hole, accomplish the procedures required by paragraph D. of this AD. \n\n\tD.\tIf any crack greater than five inches is detected, or if more than one crack on either side of BBL 0.0 is detected, they must be stop-drilled in accordance with the Boeing 727 SRM, and modified in accordance with paragraph E. of this AD. \n\n\tE.\tTo terminate the repetitive inspection requirements of paragraphs A., B., C., F., and G. of this AD, accomplish one of the following: \n\n\t\t1.\tAccomplish the modification described in Part I.D. of the Accomplishment Instructions of the service bulletin; or \n\n\t\t2.\tAccomplish the interim modification described in Part I.E. of the Accomplishment Instructions of the service bulletin. Prior to the accumulation of 12,000 landings after the incorporation of the interim modification, eddy current inspect the fastener and any stop holes for crack growth, oversize the holes, stop-drill any new cracks in accordance with the Boeing 727 SRM, and incorporate the terminating modification in accordance with Part I.E. of the Accomplishment Instructions of the service bulletin.F.\tAirplanes that have been modified prior to accumulating 20,000 landings, by installing angles back-to-back with existing stiffeners, must be inspected prior to the accumulation of 12,000 landings since the modification or within the next 1,000 landings after the effective date of this Amendment, whichever occurs later, in accordance with Figure 1 of the service bulletin. If cracks are found, before further flight, accomplish paragraph B., C., or D. of this AD, as appropriate. If no cracks are found, reinspect thereafter at intervals not to exceed 1,000 landings. \n\n\tG.\tAirplanes that have been modified after accumulating more than 19,999 landings, by installing angles back-to-back with existing stiffeners must be inspected within the next 1,000 landings after September 11, 1986 (the effective date of Amendment 39-5384), in accordance with Figure 1 of the service bulletin. If cracks are found, before further flight, accomplish paragraph B., C., or D. of this AD, as appropriate.If no cracks are found, reinspect thereafter at intervals not to exceed 1,000 landings. \n\n\tH.\tAn 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, Seattle Aircraft Certification Office, FAA, Transport Airplane Directorate. \n\n\tNOTE: The request should be submitted directly to the Manager, Seattle Aircraft Certification Office, and a copy sent to the cognizant FAA Principal Inspector (PI). The PI will then forward comments of concurrence to the ACO. \n\n\tI.\tSpecial 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. \n\n\tAll persons affected by this directive who have not already received the appropriate service documents from the manufacturer may obtain copies upon request to Boeing Commercial Airplane Group, P.O. Box 3707, Seattle, Washington 98124. These documents may beexamined at the FAA, Northwest Mountain Region, Transport Airplane Directorate, 1601 Lind Avenue S.W., Renton, Washington. \n\n\tThis amendment supersedes Amendment 39-5384, AD 86-18-03.\n \tThis amendment (39-6739, AD 90-20-02) becomes effective October 22, 1990.
89-23-14: 89-23-14 MCDONNELL DOUGLAS HELICOPTER COMPANY (MDHC): Amendment 39-6392. Docket No. 89-ASW-26. Applicability: Model 369 series helicopters, certificated in any category, with main rotor collective tube, P/N 369A7009-BSC; longitudinal control tube, P/N 369A7011-BSC; lateral control tube, P/N 369A7012-BSC; and tail rotor control tube, P/N 369A7007-BSC. Compliance: Required as indicated, unless already accomplished. To prevent fatigue failure of the control tubes which could result in loss of control of the helicopter, accomplish the following: (a) Within 25 hours' time in service after the effective date of this AD, and at intervals of 100 hours' time in service until the requirements of paragraph (c) are accomplished, remove and inspect for cracks the swaged ends of each main rotor collective control tube (P/N 369A7009-BSC), longitudinal control tube (P/N 369A7011-BSC), lateral control tube (P/N 369A7012-BSC), and each tail rotor control tube (P/N 369A7007-BSC)installed on a helicopter. If external cracks are observed as a result of this inspection, replace the control tube with a serviceable unit prior to further flight. NOTE: PART I of MDHC Service Information Notice DN-158.1, EN-48.1, FN-36.1, and HN-217.1 pertains to this AD. (b) Prior to installation, inspect for cracks the swaged ends of each main rotor collective control tube (P/N 369A7009-BSC), longitudinal control tube (P/N 369A7011-BSC), lateral control tube (P/N 369A7012-BSC), and tail rotor control tube (P/N 369A7007-BSC) from spares inventory. Reject control tubes found to be cracked as a result of this inspection. (c) Within 600 hours' time in service after the effective date of this AD remove and inspect each main rotor collective control tube (P/N 369A7009-BSC), longitudinal control tube (P/N 369A7011-BSC), lateral control tube (P/N 369A7012-BSC), and tail rotor control tube (P/N 369A7007-BSC) in accordance with the requirements of paragraph (a). Replace cracked tubes with BASIC (BSC) part numbers with the corresponding FAA-approved -5 configuration. Modify remaining BASIC (BSC) tubes to the corresponding FAA-approved -5 configuration before reinstallation. NOTE: PART II of MDHC Service Information Notice DN-158, EN-48, FN-36 or HN- 217 pertains to rework and reinstallation procedures. (d) In accordance with FAR Sections 21.197 and 21.199, the helicopter may be flown to a base where compliance with the AD may be accomplished. (e) An alternate method of compliance with this AD which provides an equivalent level of safety may be used if approved by the Manager, Los Angeles Aircraft Certification Office, FAA, 3229 E. Spring Street, Long Beach, California. This amendment (39-6392, AD 89-23-14) becomes effective on December 4, 1989.
72-19-01: 72-19-01 BELL: Amdt. 39-1517. Applies to Bell Models 206A, 206B, 206A-1 and 206B-1 helicopters certificated in all categories. Compliance required as indicated. To prevent possible failure of the main rotor retention strap fitting, P/N 206-010-155-7, and the main rotor retention strap pin, P/N 206-010-123-1, accomplish the following: (a) Remove and replace retention strap fittings, P/N 206-010-155-7, with 90 or more hours total time in service on the effective date of this A.D., within the next 10 hours time in service. (b) Remove and replace retention strap fittings, P/N 206-010-155-7, with less than 90 hours total time in service on the effective date of this A.D. prior to accumulating 100 hours time in service. (c) Remove and replace retention strap pins, P/N 206-010-123-1, with 90 or more hours total time in service on the effective date of this A.D. within the next 10 hours time in service. (d) Remove and replace retention strap pins, P/N 206-010-123-1, with less than 90 hours total time in service on the effective date of this A.D., prior to accumulating 100 hours time in service. (e) The requirements of paragraphs (a) and (b) are not applicable to main rotor retention strap fittings, P/N 206-010-155-11 or -15. The requirements of paragraphs (c) and (d) are not applicable to main rotor retention strap pins, P/N 206-010-123-3. This supersedes Amendment 39-1510 (37 F.R. 17544), A.D. 72-18-05, which superseded 72-17-04. This amendment becomes effective September 15, 1972.
90-11-02: 90-11-02 BOEING: Amendment 39-6601. Docket No. 89-NM-200-AD. \n\n\tApplicability: Model 747 series airplanes, listed in Boeing Alert Service Bulletin 747- 53A2317 dated December 21, 1989, certificated in any category. \n\n\tCompliance: Required within one year after the effective date of this AD, unless previously accomplished. \n\n\tTo prevent an APU fire from penetrating the APU firewall, accomplish the following: \n\n\tA.\tVisually inspect the APU firewall penetration located near Buttock Line Zero and Water Line 355 in accordance with Boeing Alert Service Bulletin 747-53A2317 dated December 21, 1989. If the firewall penetration is found to contain an aluminum plug assembly, prior to further flight, replace the aluminum plug assembly with a titanium or the equivalent stainless steel plug assembly, in accordance with the service bulletin listed above. \n\n\tB.\tAn alternate means of compliance or adjustment of the compliance time, which provides an acceptable level of safety, may beused when approved by the Manager, Seattle Aircraft Certification Office, FAA, Northwest Mountain Region. \n\n\tNOTE: The request should be forwarded through an FAA Principal Maintenance Inspector (PMI), who will either concur or comment, and then send it to the Manager, Seattle Aircraft Certification Office. \n\n\tC.\tSpecial 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. \n\n\tAll persons affected by this directive who have not already received the appropriate service documents from the manufacturer may obtain copies upon request to Boeing Commercial Airplanes, P.O. Box 3707, Seattle, Washington 98124. These documents may be examined at the FAA, Northwest Mountain Region, Transport Airplane Directorate, 17900 Pacific Highway South, Seattle, Washington, or Seattle Aircraft Certification Office, 9010 East Marginal Way South, Seattle, Washington. \n\n\tThis amendment (39-6601, AD 90-11-02) becomes effective on June 19, 1990.
76-05-11: 76-05-11 ENSTROM: Amendment 39-2545. Applies to Enstrom Model F-28A and 280 helicopters certified in all categories with the following serial numbers: F-28A Models - S/N 03 thru 347 280 Models - S/N 1001 thru 1030 Compliance required as indicated unless already accomplished: (a) Within the next ten (10) hours time in service after the effective date of this AD remove the three (3) tail cone attach bolts and perform a dye penetrant inspection of the bolts for fatigue cracks or an equivalent inspection method approved by the Chief, Engineering and Manufacturing Branch of the Federal Aviation Administration, Great Lakes Region. Note: Particular attention should be given to the threaded area and the radius under the base of the bolt head. (b) Replace any defective bolts with a new bolt of the same part number or a stronger equivalent listed in paragraph (d) prior to further flight. (c) Tail cone bolts of the original design shall be inspected again at 50 hours from the inspection required in paragraph (a) unless replaced with the stronger bolts as listed in paragraph (d). (d) Within 110 hours time in service from the effective date of this AD unless already accomplished replace the three (3) AN bolts attaching the tail cone with the following NAS bolts: Upper attachment point - NAS146DH-24 bolt Lower attachment points - NAS146DH-22 bolt MS20002C6 washers are to be installed under the head. Care should be exercised to insure that the proper bolt grip length is maintained. (e) Torque bolts to 240 in. - lbs. and safety wire. (f) Upon compliance with paragraphs (d) and (e) the inspections listed in paragraph (c) are no longer required. Note: When installing the NAS hardware on some helicopters in the field, it may be necessary to install an additional MS20002C6 or an AN 960-616 washer on the NAS bolts. The additional washers will insure that the bolts will not bottom out on the grip portion of the bolt when torqued to the airframe. Enstrom Service Notes 0029 and 0029A pertain to this same subject. This amendment becomes effective March 18, 1976.