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93-13-10: 93-13-10 GENERAL ELECTRIC COMPANY: Amendment 39-8623. Docket 91-ANE-54.
Applicability: General Electric Company (GE) CF6-45/-50 series turbofan engines installed on but not limited to McDonnell Douglas DC-10, Airbus A300, and Boeing 747 series aircraft.
Compliance: Required as indicated, unless accomplished previously.
To prevent engine stall, aborted takeoff, or inflight engine shutdown, accomplish the following:
(a) Perform a visual and fluorescent penetrant inspection (FPI) for cracks, and perform a mechanical gage or ultrasonic thickness measurement of the stage 12 compressor disk web-to-rim transition area of the stage 11-13 compressor spool in accordance with GE CF6-50 Service Bulletin (SB) No. 72-1006, Revision 1, dated November 14, 1991, as follows:
(1) For those stage 11-13 compressor spools listed in Table 1 of GE CF6-50 SB No. 72-1006, Revision 1, dated November 14, 1991, at the next engine shop visit, within 3,500 cycles in service after the effective date of this AD, or by December 31, 1997, whichever occurs first.
(2) For all other stage 11-13 compressor spools, at the next piece-part exposure, or by December 31, 1997, whichever occurs first.
(b) For stage 11-13 compressor spools that have cracked stage 12 compressor disk web-to-rim transition areas, or that have stage 12 compressor disk web-to-rim transition areas measuring less than 0.070 inches thick, remove from service prior to further flight, and replace with a serviceable stage 11-13 compressor spool.
(c) For stage 11-13 compressor spools that have stage 12 compressor disk web-to- rim transition areas with a minimum thickness greater than or equal to 0.070 inches but less than 0.074 inches, reidentify the stage 11-13 compressor spool with a new part number in accordance with GE CF6-50 SB No. 72-1006, Revision 1, dated November 14, 1991. The reidentified stage 11-13 compressor spool has a life limit of 16,000 cycles since new (CSN).
(d) For stage 11-13 compressor spools that have stage 12 compressor disk web-to- rim transition areas with a minimum thickness of 0.074 or more inches, mark "SB 72-1006" next to the part number and serial number on the forward spacer arm in accordance with GE CF6-50 SB No. 72-1006, Revision 1, dated November 14, 1991. The life limit of this stage 11-13 compressor spool remains at 19,000 CSN.
(e) For the purpose of this AD, an engine shop visit is defined as the induction of an engine into a shop for maintenance involving the separation of a major module.
(f) An alternative method of compliance or adjustment of the compliance time that provides an acceptable level of safety may be used if approved by the Manager, Engine Certification Office. The request should be forwarded through an appropriate FAA Principal Maintenance Inspector, who may add comments and then send it to the Manager, Engine Certification Office. NOTE: Information concerning the existence of approved alternative methods of compliance withthis airworthiness directive, if any, may be obtained from the Engine Certification Office.
(g) 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.
(h) The inspection, and replacement, if necessary, shall be done in accordance with the following service bulletin:
Document No.
Pages
Revision
Date
GE CF6-50 SB
No. 72-1006
1-30
1
November 14, 1991
Total Pages: 30
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 General Electric Aircraft Engines, CF6 Distribution Clerk, Room 132, 111 Merchant Street, Cincinnati, OH 45246. Copies may be inspected at the FAA, New England Region, Office of the Assistant Chief Counsel, 12 New England Executive Park, Burlington, MA; or at the Office of the Federal Register, 800 North Capitol Street NW., suite 700, Washington, DC.
(i) This amendment becomes effective on September 21, 1993.
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92-19-16: 92-19-16 BOEING: Amendment 39-8374. Docket No. 91-NM-171-AD. \n\n\tApplicability: Model 737 series airplanes listed in Boeing Alert Service Bulletin 737-25A1283, Revision 1, dated March 19, 1992, Boeing Service Bulletin 737-25-1291, dated December 18, 1991, and Boeing Service Bulletin 737-25-1294, dated February 20, 1992; and Model 757 series airplanes listed in Boeing Alert Service Bulletin 757-25A0121, Revision 1, dated March 19, 1992, Boeing Service Bulletin 757-25-0130, dated December 18, 1991, Boeing Service Bulletin 757-25-0130, Revision 1, dated June 4, 1992, and Boeing Service Bulletin 757-53-0056, dated September 27, 1990; certificated in any category. \n\n\tCompliance: Required as indicated, unless accomplished previously. \n\n\tTo prevent overhead stowage bins from separating from their attachments and injuring passengers in the event of an accident or emergency landing, accomplish the following: \n\n\t(a)\tFor Boeing Model 737 series airplanes listed in Boeing Alert Service Bulletin 737-25A1283, Revision 1, dated March 19, 1992; and Model 757 series airplanes listed in Boeing Alert Service Bulletin 757-25A0121, Revision 1, dated March 19, 1992; accomplish paragraph (a)(1), (a)(2), or (a)(3) of this AD, as applicable: \n\n\t\t(1)\tFor overhead stowage bins defined as Phase I in Section III, Note 5.a, of the applicable alert service bulletin, or any other stowage bin that contains a life raft or video equipment: Within 8 months after the effective date of this AD, modify those bins in accordance with Section III of Boeing Alert Service Bulletin 737-25A1283, Revision 1, dated March 19, 1992; or Boeing Alert Service Bulletin 757-25A0121, Revision 1, dated March 19, 1992; as applicable. \n\n\t\t(2)\tFor overhead stowage bins defined as Phase II, III, or IV in Section III, Notes 5.b., 5.c., and 5.d., of the applicable alert service bulletin: Within 31 months after the effective date of this AD, modify those bins in accordance with Section III of Boeing Alert Service Bulletin 737-25A1283, Revision 1, dated March 19, 1992; or Boeing Alert Service Bulletin 757-25A0121, Revision 1, dated March 19, 1992; as applicable. \n\n\t\t(3)\tFor overhead stowage bins greater than 67 inches long: Within 31 months after the effective date of this AD, replace the applicable drag link and tie rod assemblies in accordance with Boeing Service Bulletin 737-25-1291, dated December 18, 1991; or Boeing Service Bulletin 757-25-0130, dated December 18, 1991, or Revision 1, dated June 4, 1992; as applicable. \n\n\t(b)\tFor Boeing Model 737 series airplanes listed in Boeing Service Bulletin 737-25-1294, dated February 20, 1992: Within 31 months after the effective date of this AD, install a doubler on the specified forty-five inch stowage compartment, in accordance with that service bulletin. \n\n\t(c)\tFor Boeing Model 757 series airplanes listed in Boeing Service Bulletin 757-53-0056, dated September 27, 1990: Within 8 months after the effective date of this AD, install a doubler/diagonal strut assembly in accordance with that service bulletin. \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), 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(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 installations, modifications, and replacement shall be done in accordance with the following Boeing service bulletins, which contain the following specified effectivepages: \n\n\nService Bulletin\nReferenced\nPage Number\nRevision Level\nShown on Page\nDate\nShown on Page \n737-25A1283,\n1-9, 11, 13-17,\n\n\nRevision 1,\n19-21, 23-24, \n\n\nMarch 19, 1992\n26-27, 29-30, \n\n\n\n32-33, 35-36, \n\n\n\n38-39, 41-42, \n\n\n\n44-45, 48-49, \n\n\n\n51-52, 55-60, \n\n\n\n246-257 \n1\nMarch 19, 1992\n\n\n\n\n\n10, 12, 18, 22,\t\n\n\n\n25, 28, 31, 34, \n\n\n\n37, 40, 43, \n\n\n\n46-47, 50, \n\n\n\n53-54, 61-245 \nOriginal\t\nSeptember 19, 1991 \n\n\n\n\n737-25-1291,\n\n\n\nDecember 18, 1991\n1-25\nOriginal\nDecember 18, 1991\n\n\n\n\n737-25-1294,\n\n\n\nFebruary 20, 1992 \n1-11\nOriginal\t\nFebruary 20, 1992\n\n\n\n\n757-25A0121,\n1-5, 7, 9-12,\n\n\nRevision 1,\n15-17, 19-20,\n\n\nMarch 19, 1992\n22-23, 25-26, \n\n\n\n28-29, 31-32, \n\n\n\n35-36, 38-41, \n\n\n\n110-115 \n1\nMarch 19, 1992\n\n\n\n\n\n6, 8, 13-14, 18,\n\n\n\n21, 24, 27, 30, \n\n\n\n33-34, 37, 42-109 \nOriginal\t\nSeptember 19, 1991\n\n\n\n\n757-25-0130,\n1-7, 12, 14-17,\n\n\n Revision 1,\n24-26,29, 31,\n\n\nJune 4, 1992\n33-35, 37, 40-43 \n1\nJune 4, 1992\n\n\n\n\n\n8-11, 13, 18-23,\n\n\n\n27-28, 30, 32, 36,\n\n\n\n38-39 \nOriginal\nDecember 18, 1991\n\n\n\n\n757-53-0056,\n\n\n\nSeptember 27, 1990 \n1-13\nOriginal\t\nSeptember 27, 1990 \n\t\t\t \nThis 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. 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 November 20, 1992.
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93-12-04: 93-12-04 PRECISE FLIGHT, INC.: Amendment 39-8610. Docket 93-NM-14-AD.
Applicability: Precise Flight, Inc., pulselite units, Model 1210-2405-2; serial numbers X00150 through X01371, inclusive; as installed in various small airplanes in accordance with Supplemental Type Certificate (STC) SA4005NM; certificated in any category.
Compliance: Required as indicated, unless accomplished previously.
To prevent the presence of smoke in the cockpit, which could prompt the pilot to initiate an emergency landing, accomplish the following:
(a) Within 12 months after the effective date of this AD, accomplish paragraph (a)(1) or (a)(2) of this AD in accordance with Precise Flight, Inc., Service Bulletin No. PL9303001, dated March 10, 1993.
(1) Remove Precise Flight, Inc., pulselite units, Model 1210-2405-2, from the airplane. Or
(2) Replace Precise Flight, Inc., pulselite units, Model 1210-2405-2, with improved pulselite units, Model 1210-2405-2A.
(b) As ofthe effective date of this AD, no person shall install a Precise Flight, Inc., pulselite unit, Model 1210-2405-2, on any airplane.
(c) An alternative method of compliance or adjustment of the compliance time that provides an acceptable level of safety may be used if approved by the Manager, Seattle Aircraft Certification Office (ACO), FAA, Transport Airplane Directorate. Operators shall submit their requests through an appropriate FAA Maintenance Inspector, who may add comments and then send it to the Manager, Seattle ACO.
NOTE: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Seattle ACO.
(d) 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.
(e) The removal and replacement shall be done in accordance with Precise Flight, Inc., Service Bulletin No. PL9303001, datedMarch 10, 1993. 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 Precise Flight, Inc., 63120 Powell Butte Road, Bend, Oregon 97701. 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.
(f) This amendment becomes effective on July 26, 1993.
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