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93-18-04: 93-18-04 AEROSPATIALE: Amendment 39-8689. Docket 93-NM-47-AD.
Applicability: Model ATR42-300 and ATR42-320 series airplanes, certificated in any category, and having the following serial numbers:
005 through 016, inclusive;
018 through 030, inclusive;
032 through 036, inclusive;
038;
040;
042;
043;
048 through 062, inclusive;
064 through 090, inclusive;
092 through 094, inclusive; and
096 through 228, inclusive.
Compliance: Required as indicated, unless accomplished previously.
To prevent loss of strength of the fuselage frames, accomplish the following:
(a) Prior to the accumulation of 18,000 total landings, or within 100 landings after the effective date of this AD, whichever occurs later, conduct a general visual inspection of fuselage frames 25 and 27 to verify the proper installation of a rivet in each of the key holes, in accordance with Aerospatiale Service Bulletin ATR42-53-0070, dated June 10, 1991; Revision 1, dated June 12,1992; or Revision 2, dated March 22, 1993.
(b) If a rivet is installed in each of the key holes, no further action is required by this AD.
(c) If a rivet is not installed in a key hole, prior to further flight, perform an eddy current inspection of the open key hole to detect cracks, in accordance with the service bulletin.
(1) If no cracks are found as a result of the eddy current inspection, prior to further flight, install a rivet in the open key hole in accordance with the service bulletin. After such installation, no further action is required by this AD.
(2) If cracks are found as a result of the eddy current inspection, prior to further flight, repair the cracks in accordance with a method approved by the Manager, Standardization Branch, ANM-113, FAA, Transport Airplane Directorate.
(d) 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, Standardization Branch, ANM-113, 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, Standardization Branch, ANM-113.
NOTE: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Standardization Branch, ANM-113.
(e) 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.
(f) The inspections and installation shall be done in accordance with the following Aerospatiale service bulletins, which contain the specified effective pages:
Service Bulletin
Referenced and Date
Page Number
Revision Level
Shown on Page
Date
Shown on Page
ATR42-53-0070
(Original)
June 10, 1991
1-13
Original
June 10, 1991
ATR42-53-0070
Revision 1
June 12, 1992
1-7,9-12
8
1
Original
June 12, 1992
June 10, 1991
ATR42-53-0070
Revision 2
March 22, 1993
1-2, 9-10
3-7, 11-12
8
2
1
Original
March 22, 1993
June 12, 1992
June 10, 1991
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 Aerospatiale, 316 Route de Bayonne, 31060 Toulouse, Cedex 03, France. 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.
(g) This amendment becomes effective on November 18, 1993.
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94-14-12: 94-14-12 Teledyne Continental Motors: Priority Letter issued on June 23, 1994. Docket No. 94-ANE-33.
Applicability: Teledyne Continental Motors (TCM) A-65-8, C-85-12, E-185-11, E-225-B, O-200, O-300-D, GO-300, IO-360-G, IO-360-K, TSIO-360, CRSIO-360-GB, O-470 B.M, O-470-L, O-470-R, O-470-U, O-470 Z.S, IO-470-C, IO-470-E, IO-470-F, IO-470-L, IO-470-N, IO-470-S, IO-470-V, IO-520-A, IO-520-B, IO-520-C, IO-520-D, IO-520-F, IO-520-K, IO-520-M, IO-520-W, TSIO-520, TSIO-520-C, TSIO-520-M, TSIO-520-N, TSIO-520-UB, GTSIO-520, IO-550-C, and R-670 reciprocating engines, installed on the following U.S. registered aircraft: N101G, N101JB, N101PQ, N1077B, N11PT, N111MK, N114R, N1162D, N1167J, N121LG, N124WN, N13159, N1344V, N1360L, N140NL, N1503S, N1556T, N1584V, N16165, N1672R, N1680R, N172CB, N1724T, N17793, N179SV, N1806F, N1818L, N182MC, N186Q, N19193, N19346, N207X, N200BD, N2051S, N2083S, N210KC, N21179, N2168N, N22FG, N2248Z, N2281T, N231KQ, N24FG, N2616N, N26560, N27G, N27326, N2841W, N2854W, N2881M, N2928B, N2995F, N3DX, N30C, N30CA, N300RS, N31CU, N313TM, N3145Y, N3153B, N323K, N3397Q, N340VV, N3499G, N35MX, N35840, N35964, N3599L, N3603L, N36319, N3700J, N39545, N4008F, N4088V, N41CU, N41032, N4105C, N4154Y, N421CW, N421EM, N421SM, N4218L, N4259B, N4302L, N4354K, N4354W, N444BJ, N4591S, N4598S, N4672B, N476KE, N4761K, N47964, N4812F, N4884J, N4895E, N5089V, N51EN, N5314T, N5357A, N5377J, N5453J, N550DF, N5517A, N555YT, N5591D, N57032, N5732X, N58BS, N5808F, N60DM, N60062, N6108F, N6158R, N6169N, N6193X, N62121, N6222F, N6278V, N6285H, N6341X, N6363K, N6421P, N65WW, N65031, N6527P, N6579M, N6664L, N6669X, N6670G, N66909, N6706G, N67249, N677PC, N6789R, N6800R, N6822R, N6837Q, N68937, N6915F, N6952M, N6992E, N704GY, N704NQ, N7125E, N714BD, N7208V, N721X, N724BE, N7248H, N7303Y, N7309Q, N732DD, N735DV, N739JG, N7405S, N758JF, N777E, N7981D, N800WB, N8103Z, N8107D, N81070, N8150Q, N8168U, N8170D, N8209M, N8241N, N8307D, N8308Z, N836BQ, N8426S, N8432Z, N8465L, N8491S, N85WB, N8501S, N8532R, N8579H, N8579M, N85797, N86VS, N8660M, N8669A, N8867T, N9099G, N9124U, N9157S, N91603, N91860, N922DK, N92465, N9410S, N9434N, N9435U, N9516Y, N9547U, N9597T, N9606Y, N96134, N9613Y, N9673L, N96761, N9764E, N9777R, N97799, N9833H, N984BC, and N9992G.
Compliance: Required as indicated, unless accomplished previously.
To prevent detonation due to low octane, which can result in severe engine damage and subsequent failure, accomplish the following:
(a) For engines that are certified to operate on only 91 or higher octane aviation gasoline (avgas) within the next 2 hours time in service (TIS) after the effective date of this airworthiness directive (AD) perform an engine teardown and analytical inspection, and replace with serviceable parts as necessary in accordance with TCM Service Bulletin (SB) No. M88-10, dated August 24, 1988.
(b) For engines that are certified to operate on 80 octane avgas, within the next 2 hours TIS after the effectivedate of this AD conduct a differential compression test on all cylinders in accordance with TCM SB No. M84-15, dated December 21, 1984, and examine the oil filter by cutting the oil filter apart and spreading the filter paper out to look for metal particles. If metal particles are present, or if one or more cylinders shows unacceptable compression as specified in TCM SB No. M84-15, dated December 21, 1984, perform an engine teardown and analytical inspection, and replace with serviceable parts as necessary in accordance with TCM SB No. M88-10, dated August 24, 1988.
(c) An alternative method of compliance or adjustment of the compliance time that provides an acceptable level of safety may be used if approved by the Manager, Engine and Propeller Standards Staff. The request should be forwarded through an appropriate FAA Maintenance Inspector, who may add comments and then send it to the Manager, Engine and Propeller Standards Staff.
NOTE: Information concerning the existence of approved alternative methods of compliance with this airworthiness directive, if any, may be obtained from the Engine and Propeller Standards Staff.
(d) Special flight permits may be issued in accordance with sections 21.197 and 21.199 of the Federal Aviation Regulations (14 CFR 21.197 and 21.199) to operate the aircraft to a location where the requirements of this AD can be accomplished.
(e) Priority Letter AD 94-14-12, issued June 23, 1994, becomes effective upon receipt.
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