Results
73-13-04: 73-13-04 TELEDYNE CONTINENTAL MOTORS: Amdt. 39-1651. Applies to the following Teledyne Continental Model engines: O-470-J REMANUFACTURED: S/N's 46949 through 47000; 202001 through 202060. O-470-K REMANUFACTURED: S/N's 49210 through 49302. O-470-L REMANUFACTURED: S/N's 69352 through 69491. O-470-R NEW: S/N's 451001 through 451285. REMANUFACTURED: 98501 through 99000; and 2120001 through 212289. Compliance required as indicated within the next five hours time in service after the effective date of this Airworthiness Directive. Unless already accomplished inspect the carburetor bowl 1/4" drain plug for security by applying 120 to 144 in. lbs. of torque. Caution should be exercised in order not to apply excessive torque. After proper torque has been applied, check for leakage or seepage. If seepage or leakage is present, remove drain plug and check for thread damage. Replace as necessary with airworthy parts. After accomplishment of the above, place an identifying yellow dot enamel or similar paint adjacent to the drain plug. This amendment is effective June 20, 1973, and was effective upon receipt for all recipients of the air mail letter dated May 25, 1973, which contained this amendment.
70-23-05: 70-23-05 AEROSTAR: Amdt. 39-1110. Applies to all Model 600 and 601 airplanes, serial numbers 60-0001 through 60-0056 and 61-0001 through 61-0070. Compliance required as indicated, unless already accomplished. To prevent fuel discharge into the engine compartment and possible engine fire, accomplish the following: 1. Before further flight after the effective date of this AD, inspect each of the two Edison P/N 195-10TC112D1 fuel pressure indicators for a ruptured diaphragm by disconnecting and observing the fuel pressure gage vent line while operating the appropriate electric fuel pump. If fuel is found in the vent line or flows from vent, replace gage. 2. Within the next 25 hours time in service after the effective date of this AD, install fuel float check valves, Aerostar Part Number A6601151, in accordance with instruction 11 of Aerostar Aircraft Corporation Service Bulletin No. 600-28, dated November 4, 1970, or later FAA approved revision. Alternate means of compliance or equivalent replacement parts may be acceptable if approved by the Chief, Engineering and Manufacturing Branch, Flight Standards Division, Southwest Region, Federal Aviation Administration, Fort Worth, Texas. This amendment becomes effective to all known owners of Aerostar Model 600 and 601 airplanes upon receipt of individual copies mailed November 6, 1970, and to all other persons on November 16, 1970.
67-22-04: 67-22-04 BRITISH AIRCRAFT: Amdt 39-450 as amended by Amdt. Number 39-912. Applies to Model BAC 1-11 200 and 400 Series Airplanes. Compliance required as indicated. To detect failures of joints in the secondary flap transmission shafts, accomplish the following: (a) On BAC 1-11 200 Series airplanes only, within the next 150 hours' time in service after the effective date of this AD, unless already accomplished, inspect all flap secondary transmission support bearing assemblies in accordance with British Aircraft Corporation (BAC) 1-11 Alert Service Bulletin No. 27-A-PM 1928, Issue 3, or later ARB-approved issue, or FAA- approved equivalent. All defective bearing assemblies must be replaced before further flight in accordance with this Service Bulletin, or FAA-approved equivalent. Non-defective bearing assemblies may be continued in service without further inspection. (b) On BAC 1-11 200 and 400 Series airplanes, within the next 150 hours' time in service after theeffective date of this AD, unless already accomplished within the last 450 hours' time in service and thereafter at intervals not to exceed 600 hours' time in service from the last inspection, conduct a functional check of the flap secondary transmission system followed by a visual examination of the transmission shaft joints as detailed in British Aircraft Corporation Alert Service Bulletin No. 27-A-PM 1928, Issue 3, or later ARB-approved issue, of FAA- approved equivalent. Correct defects found before further flight. (c) The repetitive functional check and inspections required in paragraph (b) may be discontinued if the airplanes are modified in accordance with BAC Service Bulletin 27-PM-1928 paragraphs (a) and (b) and BAC Service Bulletin PM-2720 (a) and (b), or modified in accordance with BAC Service Bulletin PM-2720 (a), (b), (c), and (d), or FAA-approved equivalent. (d) Upon request of the operator, and FAA maintenance inspector, subject to prior approval of the Chief, Aircraft Certification Staff, FAA Europe, Africa, and Middle East Region may adjust the repetitive inspection intervals specified in this AD to permit compliance at an established inspection period of the operator if the request contains substantiating data to justify the increase for that operator. Amendment 39-450 effective August 19, 1967. This amendment (39-912) becomes effective January 11, 1970.
67-20-01: 67-20-01 ALLISON - AERO PRODUCTS: Amdt. No. 39-439 as revised Amdt. 39-466, Part 39, Federal Register June 29, 1967. Applies to Models A6441FN-606 and A6441FN-606A Propellers. Compliance required as indicated, unless already accomplished. To prevent serious overspeeds and to make the propeller pitch lock more effective under remote combinations of critical component failures, accomplish the following: (a) On or before November 1, 1967, install Part No. 6859637 restrictor in the increase pitch port of each hub island, as outlined in Allison Commercial Service Letter CSL 189, Pages 14 and 15, Paragraph C2b(1)(2)(3) and (4), entitled "Hub Assembly - Preparation for Assembly." (b) On or before November 1, 1967, remove the eight master gear retention bolts and install eight P/N 6859881 bolts as replacements, as outlined in Allison's Commercial Propeller Bulletin, CPB No. 63-317. This amendment effective August 23, 1967. Revised August 23, 1967.
91-04-08: 91-04-08 AEROSPATIALE: Amendment 39-6898. Docket No. 90-NM-226-AD. Applicability: Model ATR42-300 and ATR42-320 series airplanes, Serial Numbers 123 through 142, which have been fitted with Modification 1848 and have not incorporated Modification 2311, certificated in any category. Compliance: Required as indicated, unless previously accomplished. To prevent loss of cockpit voice recorder (CVR) information, accomplish the following: A. Within 30 days after the effective date of this AD, restore the automatic shut-off feature to the CVR by rewiring relay 9RK, in accordance with Aerospatiale Service Bulletin ATR42-23-0018, dated July 13, 1989. B. 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, Transport Airplane Directorate. NOTE: The request should be submitted directly to the Manager, Standardization Branch, ANM-113, and a copy sent to the cognizant FAA Principal Inspector (PI). The PI will then forward comments or concurrence 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. All persons affected by this directive who have not already received the appropriate service documents from the manufacturer may obtain copies upon request to Aerospatiale, 316 Route de Bayonne, 31060 Toulouse, Cedex 03, France. These documents may be examined at the FAA, Northwest Mountain Region, Transport Airplane Directorate, 1601 Lind Avenue S.W., Renton, Washington. This amendment (39-6898, AD 91-04-08) becomes effective on March 22, 1991.
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.
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.
92-27-04: 92-27-04 BOEING: Amendment 39-8437. Docket 92-NM-89-AD. \n\n\tApplicability: Model 747 series airplanes; as listed in Section 4 of Boeing Document Number D6-35999, "Aging Airplane Service Bulletin Structural Modification and Inspection Program," Revision C, dated January 21, 1992; certificated in any category. \n\n\tCompliance: Required as indicated, unless accomplished previously. \n\n\tTo prevent degradation of the structural capability of the airplane, accomplish the following: \n\n\tNOTE: Refer only to Section 4 of Boeing Document D6-35999; the appendices are not the subject of this AD. \n\n\t(a)\tExcept as provided in paragraph (e) of this AD, accomplish the inspections specified in Section 4 of Boeing Document No. D6-35999, Revision C, dated January 21, 1992, within the times specified in paragraph (b) of this AD, and thereafter at intervals not to exceed those specified in the corresponding service bulletin for the inspection. \n\n\t(b)\tThe maximum initial inspection times forthe inspections contained in Section 4 of Boeing Document No. D6-35999, Revision C, dated January 21, 1992, shall be the later of the time specified in either paragraph (b)(1) or (b)(2) of this AD: \n\n\t\t(1)\tThe threshold for the inspection time for the inspections specified in the corresponding service bulletin, measured as a total (flight cycles, time-in-service, as appropriate) accumulated on the airplane; or \n\n\t\t(2)\tThe phase-in period for the inspections specified in the corresponding service bulletin, measured from the effective date of this AD. \n\n\t(c)\tIf any of the discrepant conditions identified in the service bulletins are found as a result of the inspections required by this AD, the corresponding corrective actions specified in the service bulletins must be accomplished prior to further flight. \n\n\t(d)\tThe terminating action for each inspection required by paragraph (a) of this AD consists of the accomplishment of the modification specified in the corresponding servicebulletin. \n\n\t(e)\tNotwithstanding the references in Section 4 of Boeing Document No. D6-35999, Revision C, dated January 21, 1992, to the following list of service bulletins, this AD does not require inspections in accordance with those service bulletins: \n\n\nSERVICE BULLETIN NUMBER\nREVISION LEVEL\nSERVICE BULLETIN DATE \n747-27A2253\n4\nJanuary 25, 1990 \n747-32-2190\n4\nOctober 26, 1989 \n747-53-2253\n2\nMarch 29, 1990 \n747-53-2265\n7\nJanuary 25, 1990 \n747-53-2283\n3\nNovember 1, 1989 \n747-53-2289\n1\nJanuary 26, 1989 \n747-52-2186\n4\nOctober 24, 1991 \n747-57-2231\n2\nSeptember 27, 1990 \n\n\t(f)\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), FAA, Transport Airplane Directorate. 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(g)\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(h)\tThe inspections and corrective actions shall be done in accordance with Section 4 of Boeing Document No. D6-35999, Revision C, dated January 21, 1992, which contains the following list of effective pages: \n\n\tNOTE: Except for the title page of the document, no other pages of the document are dated. \n\n\nPage Number\nRevision Level \nShown on Page \na, c, d, d.1, e, f,\n2.0.1, 3.1.1, 3.2.1, \n3.2.2, 3.2.3, 3.3.1, \n3.4.1, 4.0.1, 4.1.1, \n4.2.1, 4.2.2, 4.3.1, \n4.3.2, 4.3.3, 5.1.1, \n5.1.2, A.3.1, B.1.1, \nB.2.1, B.3.1, B.4.1 \nC \n\n\n3.0.1, A.1.1, A.2.1 \nB \n\n\n1.2.2, 5.0.1 \nA \n\n\nb, 1.1.1, 1.2.1, 2.0.2,\n(Original)This incorporation by reference was previously approved by the Director of the Federal Register in accordance with 5 U.S.C. 552(a) and 1 CFR Part 51, as of January 20, 1993 (57 FR 59801, December 16, 1992). Copies may be obtained from Boeing Commercial Airplane Group, P.O. Box 3707, Seattle, Washington 98124. 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(i)\tThis amendment is effective January 20, 1993.
56-02-01: 56-02-01 AERO COMMANDER: Applies to Model 560A Aircraft, Serial Numbers 231 Through 269. Compliance required by April 1, 1956. Due to loss of an augmenter tube in flight, new type support clamps are required at the aft end of the augmenter tubes and at nacelle frames 148.75 and 158.75. Also, new support clips bolted through the augmenter tube at the aft end are required. Parts will be furnished by Aero Design and the rework is described in Aero Commander Service Bulletin No. 31. This supersedes CAA telegram of December 5, 1955, which required immediate inspection and installation of a 10-32 machine screw through the bell mouth and augmenter tube.