Results
76-06-10: 76-06-10 HAWKER SIDDELEY AVIATION, LTD: Amendment 39-2561. Applies to Model DH-104 "Dove" airplanes certificated in all categories which have not been modified in accordance with Dove Modification 1728. Compliance is required as indicated. To detect cracks in the nose landing gear inner casting, which could result in failure of the casing and collapse of the nose gear, accomplish the following: (a) For inner casings (P/N's 4UN.443ND and 4UN.555A) which have not been modified in accordance with either Dove Modification 847 or Modification 1008, comply with the following: (1) Locate and identify the inner casings in accordance with the instructions contained in paragraph 3.1 of Hawker Siddeley Aviation Technical News Sheet, Series CT(104), No. 232, Issue 1, dated September 17, 1973. (2) Within the next 50 hours time in service after the effective date of this AD, unless already accomplished within the preceding 600 hours time in service, and thereafter atintervals not to exceed 600 hours time in service from the last inspection, inspect the nose landing gear inner casing for cracks in accordance with paragraph 3.5 of Hawker Siddeley Aviation Ltd., Technical News Sheet, Series CT(104), No. 232, Issue 1, dated September 17, 1973, or an FAA approved equivalent. (3) If any cracks are found during an inspection required by paragraph (a)(2) of this AD, before further flight, except that the airplane may be flown in accordance with FAR's 21.197 and 21.199 to a base where the repair can be performed, replace the inner casing with a new part of the same part number or a serviceable used part of the same part number that has been inspected and found to be free of cracks in accordance with the inspection prescribed in paragraph (a)(2) of this AD. Inspect the replacement casing for cracks in accordance with paragraph 3.5 of Hawker Siddeley Aviation Ltd., Technical News Sheet Series CT(104), No 232, Issue 1, dated September 17, 1973, or an FAA-approved equivalent, within the next 600 hours time in service from time of replacement and thereafter at intervals not to exceed 600 hours time in service from the last inspection. (b) For inner casings (P/N's 14UN.467A/ND and 14UN.469A/ND) which have been modified in accordance with either Modification 847 or Modification 1008, comply with the following: (1) Within the next 50 hours time in service after the effective date of this AD, unless already accomplished within the preceding 600 hours time in service, and thereafter at intervals not to exceed 600 hours time in service from the last inspection, inspect the nose landing gear inner casings for cracks in accordance with paragraph 4.1 of Hawker Siddeley Aviation Ltd., Technical News Sheet, Series CT(104), No. 232, Issue 1, dated September 17, 1975, or an FAA approved equivalent. (2) If any cracks are found during an inspection required by paragraph (b)(1) of this AD, before further flight, except that the airplane may be flown in accordance with FAR's 21.197 and 21.199 to a base where the repair can be performed, replace the inner casing with a new part of the same part number or a serviceable used part of the same part number that has been inspected and found to be free of cracks in accordance with the inspection prescribed in paragraph (b)(1) of this AD. Inspect the replacement casing for cracks in accordance with paragraph 4.1 of Hawker Siddeley Aviation Ltd., Technical News Sheet, Series CT(104), No. 232, Issue 1, dated September 17, 1975, or an FAA approved equivalent, within the next 600 hours time in service from time of replacement and thereafter at intervals not to exceed 600 hours time in service from the last inspection. This amendment becomes effective on April 8, 1976.
77-15-10: 77-15-10 FILOTECNICA SALMOIRAGHI (AERITALIA S.p.A.): Amendment 39-2982. Applies to airspeed indicators, serial numbers 3800 and below, with part numbers - P/N 8.039.003 P/N 8.039.608.1 8.039.008 8.039.703 8.039.008.1 8.039.708 8.039.503 8.039.708.1 8.039.508 8.039.808 8.039.508.1 8.039.808.1 8.039.603 8.039.408 8.039.608 8.039.408.1 Compliance is required within the next 25 hours time in service after the effective date of this AD, unless already accomplished. To prevent the possibility of erroneous airspeed indications, accomplish the following: (a) Inspect the affected airspeed indicators for proper calibration by ensuring that the differential pressure values and tolerances for the indicator's airspeed range conform to those set forth in Tables I and II of SAE Aeronautical Standard AS-391B "Airspeed Indicator (Pitot Static)," dated December 15, 1954, or an FAA-approved equivalent. (b) If an airspeed indicator inspected in accordance with paragraph (a) of this AD is found not to be in proper calibration, scrap it. This amendment becomes effective August 4, 1977.
78-17-06: 78-17-06 PRATT & WHITNEY AIRCRAFT OF CANADA, LIMITED: Amendment 39-3286. Applies to all Pratt & Whitney Aircraft of Canada, Limited JT15D-4 engines prior to Serial Number PCE-70111 and Pratt & Whitney Aircraft JT15D-4 engines prior to Serial Number P-70111 with Part Number 3023031 and 3023035 fuel manifold adapter assemblies. Compliance required within the next 50 hours in service after the effective date of this AD, unless already accomplished. To preclude fuel leakage from the fuel adapter assemblies, replace the Part Number 3023031 and 3023035 fuel manifold adapter assemblies with Part Number 3021699 and 3021698 fuel manifold adapter assemblies in accordance with Paragraph 2, Accomplishment Instructions in Pratt & Whitney Aircraft of Canada, Limited Service Bulletin No. 7087 as revised or approved equivalent parts. Aircraft may be flown to a base for performance of maintenance required by this AD per FAR 21.197 or FAR 21.199. All equivalent parts must be approved by the Chief, Engineering and Manufacturing Branch of the Eastern Region of the Federal Aviation Administration (FAA). This amendment is effective August 31, 1978.
96-22-07: This amendment adopts a new airworthiness directive (AD), applicable to certain Jetstream Model 4100 series airplanes, that requires replacement of the existing decompression panel on the aft bulkhead of the toilet compartment with a modified decompression panel. This amendment is prompted by a report that a decompression panel that does not meet flammability requirements was installed on these airplanes during manufacture. The actions specified by this AD are intended to prevent injury to the crew and passengers and damage to the airplane structure due to the incapability of the decompression panel to contain a fire.
92-10-02: 92-10-02 BRITISH AEROSPACE: Amendment 39-8235. Docket No. 91-NM-279-AD. Applicability: Model BAe 146-100A, -200A, and -300A series airplanes, certificated in any category. Compliance: Required as indicated, unless accomplished previously. To prevent loss of all radio communication, accomplish the following: (a) Within 60 days after the effective date of this AD, remove Capacitor C68 (2.2uF, 35V) from the central audio unit station selector boards in accordance with British Aerospace Modification Service Bulletin SB.23-36-01238A, dated December 21, 1990. (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. 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. (c) 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. (d) The modification shall be done in accordance with British Aerospace Modification Service Bulletin SB.23-36-01238A, dated December 21, 1990, certificated in any category. 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. (e) This amendment becomes effective on June 11, 1992.
89-21-04 R1: 89-21-04 R1 BOEING: Amendment 39-6349 as corrected by Amendment 39-6549. Docket No. 88-NM-201-AD. \n\n\tApplicability: Model 767 series airplanes, equipped with Pratt and Whitney JT9D series engines or General Electric CF6-80A series engines, specified in Boeing Service Bulletin 767- 71-0041, dated September 22, 1988, certificated in any category.\n \n\tCompliance: Required within 15 months after the effective date of this AD, unless previously accomplished. \n\n\tTo minimize the potential for a thrust loss greater than the loss of one engine due to a lightning strike, accomplish the following: \n\n\tA.\tModify the engine electrical and electronic engine control wiring in accordance with Boeing Service Bulletin 767-71-0041, dated September 22, 1988; Revision 1, dated April 6, 1989; or Revision 2, dated June 29, 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 at the Seattle Aircraft Certification Office, 9010 East Marginal Way South, Seattle, Washington. \n\n\tThe effective date for the requirements of this amendment remains November 8, 1989, as specified in Amendment 39-6349, AD 89-21-04. \n\n\tThis AD revises AD 89-21-04, Amendment 39-6349. \n\tThis amendment (39-6549, AD 89-21-04 R1) becomes effective on March 29, 1990.
72-18-04: 72-18-04 HUGHES: Amendment 39-1509. Applies to Model 369H Series; Model 369HE, Serial Nos. 0101E thru 0215E, Model 369HM, Serial Nos. 0101M thru 0213M, Model 369HS, Serial Nos. 0101S thru 0357S Helicopters certified in all categories. Compliance required within the next 25 hours time in service after the effective date of this AD, unless already accomplished. To eliminate the possibility of exceeding the correct Vne limitations above 3000 feet density altitude, accomplish the following: (a) Install new Vne placards in accordance with Hughes Service Information Notice No. HN-45, dated 29 February 1972, or later FAA-approved revisions, or an equivalent installation approved by the Chief, Aircraft Engineering Division, FAA Western Region. New placards are available from the Manufacturer and Service Centers. (b) Revise Rotorcraft Flight Manual with RFM revision dated 2 November 1971. RFM revisions are available from the Manufacturer and Service Centers. This amendment becomes effective August 31, 1972.
90-25-04: 90-25-04 McDONNELL DOUGLAS: Amendment 39-6817. Docket No. 90-NM-71-AD. \n\n\tApplicability: Models DC-9-81, -82, -83 and -87 (MD-81, -82, -83, and -87) series airplanes, and Model MD-88 series airplanes, certificated in any category. \n\n\tCompliance: Required as indicated, unless accomplished since December 21, 1989. \n\n\tTo prevent the engine from departing the aircraft during a hard landing, in the event of a sudden engine seizure, or during flight when high velocity vertical gust is encountered, accomplish the following: \n\n\tA.\tWithin 30 days after the effective date of this AD, accomplish the following: \n\n\t\t1.\tPerform one of the following inspections: \n\n\t\t\ta.\tPerform a one-time visual inspection of both the left and right engine forward mount cone bolts for the correct part number, in accordance with McDonnell Douglas MD-80 Alert Service Bulletin A71-49, Revision 2, dated November 4, 1990 (from hereon referred to as the Service Bulletin). If the part number of the cone bolt is other than "Barry" Part Number K2219-9SA3 or McDonnell Douglas Part Number 7938004-503, prior to further flight, remove and replace the bolt with a "Barry" Part Number K2219-9SA3 or McDonnell Douglas Part Number 7938004-503 cone bolt; or \n\n\t\t\tb.\tPerform a one-time ultrasonic inspection of both the left and right engine forward mount cone bolts in accordance with the Service Bulletin. If the part shows an indication of shear section cut-out, remove and replace the bolt with a "Barry" Part Number K2219-9SA3 or McDonnell Douglas Part Number 7938004-503 cone bolt. \n\n\t\t2.\tIncorporate a revision into the FAA-approved maintenance inspection program which provides for a visual or ultrasonic inspection of the engine forward mount cone bolts for "Barry" Part Number K2219-9SA3, or McDonnell Douglas Part Number 7938004-503, at each engine change and, if incorrect bolts are found, replace with "Barry" Part Number K2219-9SA3 or McDonnell Douglas Part Number 7938004-503 bolts before eachengine installation. \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, Los Angeles Aircraft Certification Office (ACO), FAA, Transport Airplane Directorate. \n\n\tNOTE: The request should be submitted directly to the Manager, Los Angeles ACO, and a copy sent to the cognizant FAA Principal Inspector (PI). The PI will then forward comments or concurrence to the Los Angeles ACO. \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 McDonnell Douglas Corporation, 3855 Lakewood Boulevard, Long Beach, California 90846, Attention: Business Unit Manager of Publications, C1-HCW (54-60). These documentsmay be examined at the FAA, Northwest Mountain Region, Transport Airplane Directorate, 1601 Lind Avenue S.W., Renton, Washington, or the Los Angeles Aircraft Certification Office, 3229 East Spring Street, Long Beach, California. \n\n\tThis amendment (39-6817, AD 90-25-04) becomes effective January 2, 1991.
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.