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74-24-05: 74-24-05 AIRESEARCH MANUFACTURING COMPANY OF ARIZONA: Amendment 39-2017. Applies to AiResearch Model TPE331 Series engines of the following specific models and listed serial numbers: TPE331-3U-303G; S/N 03127 through 03173 and 03176; TPE331-3UW-303G, S/N 05031 through 05042; TPE331-5-251C, S/N 22007 through 22045 and 22047 through 22050; TPE331-5-251K, S/N 06227 through 06238, 06240 through 06418 and 06420 through 06435; and, TPE 331-6-251M, S/N 20267 through 20437, 20439 through 20468 and 20470 through 20478. In addition to the above listed serial numbers, other engines of these models which have been modified by incorporation of AiResearch Service Bulletin No. TPE331-72-0055 are also affected. To determine if this service bulletin has been accomplished, refer to the engine logbook and the engine power section nameplate. The following "Power Section Change No's" indicate incorporation of this service bulletin: TPE331-3U-303G and - 3UW-303G, Ch. No. 42; TPE331-5-251C, Ch. No. 8;TPE331-5-251K, Ch. No. 25; and TPE331-6-251M, Ch. No. 18. Compliance required as indicated: To detect, correct and prevent fatigue failure of the pin in the propeller pitch control sleeve assembly accomplish the following: (A) For engines with less than 100 hours time in service or since incorporation of AiResearch Service Bulletin TPE331-72-0055: Within the next 25 hours time in service after receipt of this airmail letter, unless previously accomplished, perform the following: (1) Inspect the propeller pitch control sleeve assembly per Paragraph 2.B. or perform the vibration test per paragraph 2.C. of AiResearch Service Bulletin TPE331-72-0087, Rev. 1, dated October 29, 1974, or later FAA-approved revisions. Note: The inspection or test prescribed above need not be performed on the following listed engines since the vibration test was accomplished by the manufacturer prior to delivery: TPE331-3U-303G, S/N 03170 through 03173 and 03176; TPE331-5-251C, S/N-22047, 22048 and 22050; TPE331-5-251K, S/N 06418 and 06420 through 06435; and, TPE331-6-251M, S/N 20382, 20451, 20471 and 20473 through 20478. (2) Replace the hydraulic turbine bearing support mount retainer per paragraph 2.D. of AiResearch Service Bulletin TPE331-72-0087, Rev. 1, dated October 29, 1974, or later FAA approved revisions. (B) For engines with more than 100 hours time in service or since incorporation of AiResearch Service Bulletin TPE331-72-0055: Within the next 300 hours time in service after receipt of this airmail letter, unless previously accomplished, accomplish the inspection or test and replacement described in (A), above. (C) For new, overhauled or repaired engines not in service: Before placing these engines in service, after receipt of this airmail letter, unless previously accomplished, accomplish the inspection or test and replacement described in (A) above. (D) Equivalent procedures may be approved by the Chief, Aircraft Engineering Division, FAA Western Region, upon submission of adequate substantiation data. (E) Aircraft may be flown to a base for performance of maintenance required by this AD per FAR's 21.197 and 21.199." This amendment becomes effective November 26, 1974, for all persons except those to whom it was made effective by airmail letter dated November 1, 1974.
74-20-07 R5: 74-20-07 R5 SIKORSKY AIRCRAFT: Amendment 39-1971 as amended by Amendments 39- 1989, 39-2152, and 39-2439 is further amended by Amendment 39-4895. Applies to S-61L, S- 61N, S-61NM, and S-61R helicopters certificated in all categories, and S-61A (aircraft S/N's 61083, 61087, 61094, and 61161) and S-61V (aircraft S/N 61271) helicopters certificated in the restricted category. Compliance is required as indicated (unless already accomplished). To prevent operation with fatigue cracks in the spar of a main rotor blade, accomplish the following: (a) Remove from service within the next 10 hours time in service from the effective date of this amended AD: (1) Any main rotor blade which does not comply with Sikorsky Service Bulletin No. 61B15-6P, or later FAA-approved revisions, excluding Section 2, Accomplishment Instructions, Part II, Operation, Pilot Information. For main rotor blades which are in compliance, the service life limits are: (i) 8,000 hours total time in service for S6117-20101 series blades; (ii) 9,400 hours total time in service for S6115-20501, S6115-20601, S6188-15001, and 61170-20201 series blades; (2) Any military main rotor blade installed on a helicopter certificated in the restricted category which is not equipped with a visual blade pressure inspection system equivalent to that specified in Sikorsky Service Bulletin No. 61B15-6P, or later FAA-approved revisions. For military blades which are in compliance, the service life limits shall be those specified in the restricted category approval. (b) Inspect main rotor blades equipped with approved visual blade pressure indicators but not equipped with an in-cockpit blade inspection system, or if equipped, with the system inoperative, in accordance with paragraphs (c) and (d). For helicopters equipped with an operative in-cockpit blade inspection system, inspect the main rotor blades in accordance with paragraphs (e) and (f). (c) Within the next 3 hours time in service after the effective date of this amended AD, unless already accomplished, inspect the visual blade pressure indicators of the following blades of helicopters not equipped with an in-cockpit blade pressure monitoring system (see Sikorsky Service Bulletin No. 61B15-20D), or equipped with such system inoperative: S6115-20501 Series S6115-20601 Series S6117-20101 Series S6188-15001 Series 61170-20201 Series 61170-20201-062 (S-61A aircraft S/N's 61083 and 61094) S6115-20201-2 (S-61A aircraft S/N's 61087 and 61161) 61170-20201-060 (S-61V aircraft S/N 61271), according to the procedures set forth in Section 2, Part IV, of Sikorsky Service Bulletin No. 61B15-6P, or later FAA-approved revisions, and as supplemented by paragraph (d) of this AD. (1) Conduct visual inspections or checks of blade-mounted pressure indicators from the transmission work platform of the helicopter to ensure that an accurate visual check is conducted. (2) The visual inspections or checks ofblade-mounted pressure indicators shall be conducted by an individual who holds a pilot certificate with appropriate rating or a mechanic certificate with airframe rating or by a certificated maintenance entity. The person performing this inspection or check shall make entries of the results in the aircraft maintenance record including a description and date of the inspection and the name of the individual performing the inspection along with the certificate number, kind of certificate, and signature. (3) Each blade with any black or red indication visible in the blade pressure indicator is considered to be unsafe and is restricted from further flight until the cause of the indication is determined and corrected in accordance with the procedures given in Sikorsky Service Bulletin No. 61B15-6P, or later FAA-approved revisions. NOTE: The inspections that are required by paragraph (c) to be performed and recorded may be considered to be "airworthiness checks." If preventivemaintenance action in accordance with Sikorsky Service Bulletin No. 61B15-6P, or later FAA-approved revisions, is required as a result of these inspections (airworthiness checks), the subsequent inspections required are considered preventive maintenance that may be performed by persons authorized to perform preventive maintenance under Part 43 of the FAR. (d) After the initial inspections in accordance with paragraph (c), conduct further inspections in accordance with paragraph (c) prior to the first flight of each day and at intervals not to exceed 3 hours time in service from the last inspection, except for blades identified with yellow or white circles which are limited to inspection intervals of 1 and 2 hours, respectively. Helicopter time in service for any single flight in excess of the specified inspection interval is not permitted, and if the time in service since the last inspection will exceed the specified interval during the next flight, the visual inspection mustbe conducted prior to the flight. Yellow or white circles and attendant speed restrictions of AD 74-25-05 may be removed if the main rotor blade is refurbished by Sikorsky in accordance with FAA-approved procedures of June 16, 1975. (e) Prior to the first flight of the day and every 8 hours time in service thereafter for helicopters equipped with an operable in-cockpit blade pressure monitoring system (see Sikorsky Service Bulletin No. 61B15-20D), and with main rotor blades with serial numbers of 61M-6350- 6105 or greater, or which have been refurbished by Sikorsky in accordance with FAA-approved procedures of June 16, 1975, inspect the main rotor blade pressure indicators and pressure transducers of the blades specified in paragraph (c) according to the procedures set forth in Section 2, Part IV of Sikorsky Service Bulletin No. 61B15-6P, or later FAA-approved revisions. (1) The visual inspections or checks of blade-mounted pressure indicators are to be conducted from the transmission work platform of the helicopter to ensure that an accurate visual check is conducted. (2) The required functional tests and visual checks shall be conducted by an individual who holds a pilot certificate with appropriate rating or a mechanic certificate with airframe rating or by a certificated maintenance entity. The person performing these tests and checks shall make entries of the results of the inspections in the aircraft maintenance record including a description and date of the inspection and the name of the individual performing the inspection along with the certificate number, kind of certificate, and signature. (3) Each blade with any black or red indication visible in the blade pressure indicator or whose transducer activates the cockpit warning light is considered to be unsafe and is restricted from further flight until the cause of the indication is determined and corrected in accordance with procedures given in Sikorsky Service Bulletin No. 61B15-6P, orlater FAA- approved revisions. (f) After the initial inspections in accordance with paragraph (e): (1) Conduct functional tests in accordance with the procedures of paragraph (e) of all visual blade pressure indicators and in-cockpit blade inspection system transducers every 8 hours time in service. (2) Check the in-cockpit blade inspection system electrical circuit every 3 hours time in service by use of the system test switch located in the cockpit. An in-flight indication of a failure of the system electrical circuit must be treated in the same manner as an in- cockpit system warning light indication as provided in the Emergency Procedures section of the Rotorcraft Flight Manual. (g) Alternate inspections, repairs, modifications, or other means of compliance which provide an equivalent level of safety to this AD must be approved by the Manager, Boston Aircraft Certification Office, FAA, New England Region, 12 New England Executive Park, Burlington, Massachusetts 01803. In accordance with FAR Section 21.197, flight is permitted to a base where the requirements of this AD may be accomplished. (h) For helicopters equipped with an operable in-cockpit blade pressure monitoring system (see Sikorsky Service Bulletin No. 61B15-20D), inspect the main rotor blade pressure indicators and transducers of the blades specified in Paragraph (f) according to the procedures set forth in Section 2, Part IV of Sikorsky Service Bulletin No. 61B15-6P, or later FAA-approved revisions, and as supplemented by the inspection intervals specified in paragraph (g). (1) The required visual checks may be performed by the pilot. (2) Each blade whose transducer activates the cockpit warning light is considered to be unsafe and is restricted from further flight until the cause of the indication is determined and corrected in accordance with procedures given in Sikorsky Service Bulletin No. 61B15-6P, or later FAA-approved revisions. (i) Alternate inspections, repairs, modifications, or other means of compliance which provide an equivalent level of safety to this AD must be approved by the Manager, Boston Aircraft Certification Branch, FAA, New England Region, 12 New England Executive Park, Burlington, Massachusetts 01803. In accordance with FAR 21.197, flight is permitted to a base where the requirements of this AD may be accomplished. The manufacturer's specifications and procedures (Sikorsky Service Bulletin No. 61B15- 6P Revision No. 16, 12/3/81 including Revision No. 12, 6/2/77 and Revision No. 15, 4/21/80; Sikorsky Service Bulletin No. 61B15-20 Revision No. 4, 11/9/77) identified in this directive are incorporated herein and made a part hereof pursuant to 5 U.S.C. 552(a)(1). All persons affected by this directive who have not already received these documents from the manufacturer may obtain copies upon request to United Technologies Corporation, Sikorsky Aircraft Division, North Main Street, Stratford, Connecticut, 06601, Attn: S-61 Commercial Product Support Dept. These documents also may be examined in the Rules Docket at the Office of the Regional Counsel, Southwest Region, Federal Aviation Administration, Room 156, Building 3B, 4400 Blue Mound Road, Fort Worth, Texas 76106. This supersedes Amendment 39-283 (31 FR 11714), AD 66-22-5, as amended by Amendment 39-809 (34 FR 12563), Amendment 39-828 (34 FR 13969), Amendment 39-981 (35 FR 6858) and Amendment 39-1178 (36 FR 5674). Amendment 39-1971 became effective October 4, 1974. Amendment 39-1989 became effective October 24, 1974. Amendment 39-2152 became effective April 16, 1975. Amendment 39-2439 became effective December 23, 1975. This Amendment 39-4895 becomes effective September 26, 1984, as to all persons including those persons to whom part was made immediately effective by priority letter AD 74- 20-07 R4 issued December 30, 1983, which contained part of this amendment.
2017-10-07: We are adopting a new airworthiness directive (AD) for certain The Boeing Company Model 737-400 series airplanes. This AD was prompted by an evaluation by the design approval holder (DAH), which indicates that the aft fuselage skin is subject to widespread fatigue damage (WFD), and reports of aft fuselage skin cracking. This AD requires repetitive inspections to detect cracking of the aft fuselage skin, inspections to detect missing or loose fasteners and any disbonding or cracking of bonded doublers, permanent repairs of time-limited repairs, related investigative and corrective actions if necessary, and skin panel replacement. We are issuing this AD to address the unsafe condition on these products.
2017-10-11: We are adopting a new airworthiness directive (AD) for Stemme AG Model S10-VT gliders (type certificate previously held by Stemme GmbH & Co. KG). This AD results from mandatory continuing airworthiness information (MCAI) issued by the aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as certain propeller front transmission gear wheels having insufficient material strength because of improper heat treatment [[Page 24240]] during manufacturing. We are issuing this AD to require actions to address the unsafe condition on these products.
2024-16-16: The FAA is superseding Airworthiness Directive (AD) 2020-25- 07, which applied to certain Embraer S.A. Model EMB-550 and EMB-545 airplanes. AD 2020-25-07 required repetitive inspections of the flight deck side windows for any cracking or delamination, corrective action if necessary, and eventual replacement of the windows. Since the FAA issued AD 2020-25-07, additional part numbers were added to the installation prohibition list. This AD continues to require the actions in AD 2020-25-07, expands the list of affected parts, and prohibits the installation of affected parts, as specified in an Ag[ecirc]ncia Nacional de Avia[ccedil][atilde]o Civil (ANAC) AD, which is incorporated by reference. The FAA is issuing this AD to address the unsafe condition on these products.
74-18-17 R1: 74-18-17 R1 MCDONNELL DOUGLAS: Amendment 39-1985 as amended by Amendment 39-5780. Applies to DC-10-10, -15, -30, -40, and KC-10A (Military) series airplanes, certificated in any category. Compliance required as indicated, unless previously accomplished. \n\n\tTo provide additional fire protection for the Number 2 engine position in the event of fan blade fragmentation, accomplish the following: \n\n\tA.\tFor airplanes equipped with General Electric CF6 engines with one or more gun-drilled fan blades: Prior to further flight, install a fuel hose shield on the Number 2 engine in accordance with the Accomplishment Instructions of McDonnell Douglas DC-10 Service Bulletin 71-57 dated September 3, 1974, or later FAA approved revisions. \n\n\tB.\tFor all other airplanes: Within the next 12 months after the effective date of this AD, install a fuel hose shield on the Number 2 engine position in accordance with the Accomplishment Instructions of McDonnell Douglas DC-10 Service Bulletin No. 71-141, dated June 24, 1986, or later FAA-approved revisions. \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\tD.\tAlternate means of compliance which provide an acceptable level of safety may be used when approved by the Manager, Los Angeles Aircraft Certification Office, FAA, Northwest Mountain Region. \n\n\tAll persons affected by this directive who have not already received the appropriate service information from the manufacturer may obtain copies upon request to McDonnell Douglas Corporation, 3855 Lakewood Boulevard, Long Beach, California 90846, Attention: Director, Publications and Training, C1-750 (54-60). These documents may be examined at the FAA, Northwest Mountain Region, 17900 Pacific Highway South, Seattle, Washington, or the Los Angeles Aircraft Certification Office, 4344 Donald Douglas Drive, Long Beach, California. \n\n\tAmendment 39-1985 became effective October 15, 1974. \n\n\tThis amendment, 39-5780, becomes effective January 13, 1988.
75-22-05: 75-22-05 DETROIT DIESEL ALLISON: Amendment 39-2391. Applies to Detroit Diesel Allison Model 501-D13 series engines which incorporate P/N 6829072 and 6847112 second stage turbine wheels with the serial numbers listed below: Compliance required as indicated: I. Remove from service in accordance with the schedule in paragraphs I.A, B, C, and D, wheels with the following serial numbers: CA-6108 CA-6112 CA-6114 CA-6056 CA-6083 KK-2052 to and including KK-2053 KK-2055 to and including KK-2085 KK-2092 to and including KK-2094 KK-2099 to and including KK-2100 KK-2102 to and including KK-2115 KK-2117 to and including KK-2167 KK-2169 to and including KK-2251 KK-2253 to and including KK-2329 KK-2332 to and including KK-2382 KK-2384 to and including KK-2460 KK-2475 to and including KK-2500 KK-2502 to and including KK-2643 KK-2645 to and including KK-2682 KK-2763 to and including KK-2813 KK-2824 to and including KK-2857 KK-2873 to and including KK-2901 KK-3033 to and including KK-3034 KK-3047 to and including KK-3048 KK-3063 to and including KK-3075 KK-3108 to and including KK-3118 KK-3136 to and including KK-3239 KK-3287 to and including KK-3300 KK-3314 to and including KK-3327 KK-3617 to and including KK-3643 KK-3756 to and including KK-3768 KK-3867 to and including KK-3880 KK-11829 to and including KK-11832 KK-16501 to and including KK-16589 KK-16901 to and including KK-16999 KK-19966 to and including KK-20064 NOTE: At time of overhaul, some wheels have R1, R2, R3, R4, or R5 added as a suffix to the wheel serial number. The suffix should be disregarded in determining the applicability of this A.D. A. Remove from service within the next 200 cycles, wheels which have 16,000 or more total cycles on the effective date of this A.D. B. Remove from service within the next 400 cycles, or prior to exceeding 16,200 total cycles, which ever comes first, wheels which have from 14,000 to 16,000 total cycles on the effective date of this A.D. C. Remove from service within the next 500 cycles, or prior to exceeding 14,400 total cycles whichever comes first, wheels which have 13,500 to 14,000 total cycles on the effective date of this A.D. D. Remove from service prior to exceeding 14,000 total cycles, wheels which have less than 13,500 total cycles on the effective date of this A.D. II. Remove from service in accordance with the schedule in paragraphs II A, B, C, D, E and F, wheels with the following serial numbers: KK-3132 and KK-15499 KK-29611 to and including KK-2997 KK-3035 to and including KK-3046 KK-3049 to and including KK-3062 KK-3076 to and including KK-3107 KK-3119 to and including KK-3130 KK-3240 to and including KK-3286 KK-3301 to and including KK-3313 KK-3328 to and including KK-3364 KK-3376 to and includingKK-3580 KK-3582 to and including KK-3616 KK-3644 to and including KK-3755 KK-3769 to and including KK-3782 KK-3798 to and including KK-3866 KK-3881 to and including KK-3949 KK-3963 to and including KK-3976 KK-3996 to and including KK-4006 KK-1180 to and including KK-11821 KK-14201 to and including KK-14207 KK-14466 to and including KK-14470 KK-14801 to and including KK-14815 KK-15704 to and including KK-15784 KK-20577 to and including KK-20680 KK-21599 to and including KK-21653 A. Remove from service within the next 200 cycles, wheels which have 16,000 or more total cycles on the effective date of this A.D. B. Remove from service within the next 400 cycles, or prior to exceeding 16,200 total cycles, whichever comes first, wheels which have from 14,000 to 16,000 total cycles on the effective date of this A.D. C. Remove from service within the next 1000 cycles, or prior to exceeding 14,400 total cycles whichever comes first, wheels which have 10,500 to 14,000 total cycles on the effective date of this A.D. D. Remove from service within the next 2,000 cycles, or prior to exceeding 11,500 total cycles, whichever comes first, wheels which have from 7,000 to 10,500 total cycles on the effective date of this A.D. E. Remove from service within the next 2,100 cycles, or prior to exceeding 9,000 total cycles, whichever comes first, wheels which have from 4,900 to 7,000 total cycles on the effective date of this A.D. F. Remove from service prior to exceeding 7,000 total cycles, wheels with less than 4,900 total cycles on the effective date of this A.D. III. Remove from service in accordance with the schedule in paragraphs III A, and B, wheels with serial numbers not specified in Paragraphs I or II above, or in AD 75-17-32 (Amdt. 39-2336). A. Remove from service within the next 100 cycles, wheels which have 6900 or more total cycles on the effective date of this A.D. B. Removefrom service prior to exceeding 7,000 total cycles, wheels which have less than 6,900 total cycles on the effective date of this A.D. IV. Wheels removed per paragraphs I, II or III above, which have less than 14,000 total cycles may be inspected as specified in IV.A and B, and if found satisfactory, may be returned to service until they reach the total number of cycles specified in IV.C; however, no wheels may exceed 11,000 total hours in service. A. Inspect for hub spline cracks using fluorescent penetrant method FP-30A or ZL-30A. B. Inspect and classify microstructure per Detroit Diesel Allison 501-D13 Commercial Overhaul Information Letter No. COIL-349. C. Wheels inspected and classified per IV.A and B above, may be continued in service as follows: 1. Light carbide and medium light carbide wheels may be operated for a maximum of 14,000 cycles total. 2. Medium heavy carbide wheels may be operated for 7,000 cycles between inspections per IV.A andB above, for a maximum of 14,000 total cycles. 3. Heavy carbide wheels may not be operated more than 7,000 total cycles maximum. V. For the purposes of this airworthiness directive, a cycle is defined as one takeoff. VI. Detroit Diesel Allison 501-D13 Commercial Service Letter No. CSL-235 pertains to this subject. The manufacturer's service letter identified and described in this directive is incorporated herein and made a part hereof pursuant to 5 U.S.C. 552(a)(1). All persons affected by this directive who have not already received this document from the manufacturer may obtain copies upon request to Detroit Diesel Allison, Division of General Motors Corporation, P. O. Box 894, Indianapolis, Indiana, 46206. This document may also be examined at the Office of the Regional Counsel, Federal Aviation Administration, Great Lakes Region, 2300 East Devon Avenue, Des Plaines, Illinois, 60018, and at Federal Aviation Administration Headquarters, 800 Independence Avenue, S.W., Washington, D.C., 20591. A historical file on this AD which includes the incorporated material in full is maintained by the Federal Aviation Administration at its headquarters in Washington, D.C., and at the Great Lakes Regional Office in Des Plaines, Illinois. This supersedes Amendment 39-2117, Airworthiness Directive 75-05-15. This amendment is effective October 23, 1975.
71-05-02: 71-05-02 AVCO LYCOMING: Amdt. 39-1158 as amended by Amendment 39-1402, 39-1537 and 39-1550 is further amended by Amendment 39-1589. Applies to all IO-360-A and -C series engines except S/N 7100-51A and subsequent and except all engines overhauled (also known as remanufactured) by Lycoming after 26 January 1970 except S/N 354-51, 1049-51A, 3003-51A, 3281-51A, 6526-51A. To prevent shifting and possible failures of the crankcase main bearings, perform the following: (a) Engines that have accumulated less than 500 hours in service since new or overhaul must have the lubrication system inspected for metal contaminants within the next 10 hours in service after the effective date of this AD and every 25 hours in service until 525 hours in service are accumulated, at which time compliance with (d) or (f) is required. Inspection of the lubrication system consists of visual examination for minute particles of metal suspended in the oil, examination of the engine oil suction screen for presence of metal particles and the inspection of the external full flow oil filter for metal particles by cutting it open so that the pleated element can be unfolded and examined. (b) Engines that have accumulated 500 hours or more in service since new or overhaul must have the lubrication system inspected for metal contaminants within the next 10 hours in service after the effective date of this AD. Further, compliance with (d) or (f) is required within 25 hours in service after the effective date of this AD. (c) Compliance with (d) or (f) is required if metal contaminants are detected during the above inspections. (d) Remove number two position cylinder and examine visually the position of the center main bearing for shifting in accordance with the inspection procedure of Avco Lycoming Service Bulletin No. 327B or equivalent inspection approved by Chief, Engineering and Manufacturing Branch FAA, Eastern Region. Should shifting be detected, comply with paragraph (f). If thebearing has not shifted and no metal contaminants are detected after compliance with paragraph (a) or (b) the engine can be returned to service and the lubrication system must be inspected for contaminants every 50 hours in service thereafter. (e) Unless already accomplished, compliance with paragraph (f) is required within 50 hours in service after the effective date of this AD on engines that have accumulated 1150 hours or more in service since new or last overhaul. (f) Modify the crankcase as described in Lycoming Service Instructions No. 1123A or repair the crankcase as described in Lycoming Service Instructions No. 1112C, whichever is applicable, and install straight crankcase bearing dowels per Lycoming Service Bulletin No. 326 or equivalent repair or alteration approved by Chief, Engineering and Manufacturing Branch, FAA, Eastern Region. Compliance with the provisions of this paragraph eliminates the inspection requirements of this AD. (NOTE: The inspection of the lubrication system required by this AD constitutes preventive maintenance.) Amendment 39-1158 was effective February 23, 1971. Amendment 39-1402 was effective March 14, 1972. Amendment 39-1537 was effective October 17, 1972. Amendment 39-1550 was effective upon publication in the Federal Register. This amendment 39-1589 is effective February 13, 1973.
2017-10-18: We are adopting a new airworthiness directive (AD) for all Airbus Model A330-223F, -223, -321, -322, and -323 airplanes. This AD was prompted by fatigue load analysis that determined the need for reduced inspection intervals and updated torque values of the bolts. This AD requires repetitive torque checks of the forward engine mount bolts, an inspection of the forward mount assembly, and replacement of the bolts or repair of the forward mount assembly as necessary. We are issuing this AD to address the unsafe condition on these products.
2017-10-06: We are adopting a new airworthiness directive (AD) for certain Rolls-Royce plc (RR) RB211 Trent 768-60, 772-60, and 772B-60 turbofan engines. This AD requires fluorescent penetrant inspection (FPI) of the compressor intermediate case (CIC) for cracking. This AD was prompted by CICs that were weld repaired and have a higher probability of cracking as a result of the weld repair process. We are issuing this AD to correct the unsafe condition on these products.
2024-16-18: The FAA is adopting a new airworthiness directive (AD) for certain Bombardier, Inc., Model BD-100-1A10 airplanes. This AD was prompted by a determination that a revised restrictive airworthiness limitation is necessary. This AD requires revising the existing maintenance or inspection program, as applicable, to incorporate a revised restrictive airworthiness limitation for the aft engine mount attachment bolts. The FAA is issuing this AD to address the unsafe condition on these products.
71-19-06: 71-19-06 HAWKER SIDDELEY: Amdt. 39-1294. Applies to Model DH-104 "Dove" airplanes. Compliance is required as indicated. To ensure that the emergency escape hatches (P/N's 4FS.835A/I and 4FS.835A/2) can be opened from outside the airplane accomplish the following: (a) Before further flight check the operation of each escape hatch lock mechanism by turning the external handle with the internal handle in the stowed position. The check required by this paragraph may be performed by the pilot. (b) If an escape hatch lock mechanism is found to be inoperable during the check required by paragraph (a), before further flight, except that the airplane may be flown in accordance with FAR 21.197 to a base where the repairs can be performed, secure the inoperable lock mechanism to the escape hatch in accordance with Hawker Siddeley Technical News sheet Series: CT(104) No. 222, Issue 1, dated March 15, 1971, or an FAA approved equivalent. (c) Within the next 100 hourstime in service after the effective date of this AD, unless already accomplished, secure the lock mechanism to each escape hatch in accordance with Hawker Siddeley Aviation, Ltd., Technical News Sheet Series: CT(104) No. 222, Issue 1, dated March 15, 1971, or an FAA-approved equivalent. This amendment becomes effective September 21, 1971.
71-24-03: 71-24-03 PRATT & WHITNEY ENGINES: Amdt. 39-1335 as amended by Amendment 39-1365 and 39- 1401 is further amended by Amendment 39-1447. Applies to all Pratt & Whitney Aircraft JT9D-3A turbofan engines which incorporate Part Number 669647 diffuser case assembly. Compliance required as indicated. To preclude rupture of the part number 669647 diffuser case assembly as the result of borescope boss weld cracks, accomplish the following: 1. For wet operating JT9D-3A engines with diffuser cases having in excess of 2500 hours or 600 cycles time in service, inspect all borescope positions in accordance with paragraph 4 within 25 cycles after the effective date of this AD and every 25 cycles thereafter. 2. For dry operating JT9D-3A engines with diffuser cases having in excess of 2500 hours or 600 cycles in service, inspect all borescope positions in accordance with paragraph 4 within 100 cycles after the effective date of this AD or 250 cycles since the last inspection, whichever occurs later, and every 250 cycles thereafter. NOTE: For the purposes of this paragraph, JT9D-3A engines operating both wet and dry may be considered as dry operation provided each wet cycle is counted as equivalent to 10 dry cycles. 3. Inspect all borescope positions which have been weld repaired as specified in Pratt & Whitney Aircraft Alert Service Bulletin No. 2901 in accordance with paragraph 4 within the next 5 to 15 cycles after weld repair or 15 cycles after the effective date of this AD, whichever occurs later, and every 25 cycles wet operation or 250 cycles dry operation thereafter. 4. Inspect borescope boss weld areas of the Part Number 669647 diffuser case assembly using one of the techniques specified in Pratt & Whitney Aircraft Alert Service Bulletin No. 2901 or any equivalent inspection procedure approved by the FAA, Chief, Engineering and Manufacturing Branch, Eastern Region. If any crack is found, remove the diffuser case from service, and replaceor repair in accordance with Pratt & Whitney Aircraft Alert Service Bulletin No. 2901. 5. For JT9D-3A engines with diffuser cases incorporating reinforcement straps in accordance with Pratt & Whitney Aircraft Special Instruction No. 29F-71, or equivalent alteration approved by the Chief, Engineering and Manufacturing Branch, FAA, Eastern Region, inspect all borescope positions in accordance with paragraph 4 within 250 cycles after installation of the reinforcement straps and every 250 cycles thereafter. 6. Upon submission of substantiating data through an FAA maintenance inspector, the Chief, Engineering and Manufacturing Branch, FAA, Eastern Region, may adjust the repetitive inspection times specified in this airworthiness directive. 7. For JT9D-3A engines incorporating fuel nozzle and support assemblies reworked in accordance with Pratt & Whitney Aircraft Turbine Engine Service Bulletin No. 3627 or equivalent method approved by the Chief, Engineering and ManufacturingBranch, Eastern Region, inspect all borescope positions in accordance with paragraph 4 within 75 cycles after installation of the reworked fuel nozzle and support assemblies and every 75 cycles thereafter. NOTE: Turbine Engine Service Bulletin No. 3627 does not apply to engines which incorporate Turbine Engine Service Bulletin No. 3223 or 3628. Amendment 39-1335 was effective November 24, 1971, and was effective upon receipt for all recipients of the telegram dated October 8, 1971 which contained this amendment. Amendment 39-1365 was effective December 31, 1971. Amendment 39-1401 was effective March 14, 1972. This Amendment 39-1447 is effective May 19, 1972.
2017-10-24: We are superseding Airworthiness Directive (AD) 2011-17- [[Page 24036]] 09 for all Airbus Model A330-200, -200 Freighter, and -300 series airplanes; and AD 2012-25-12 for all Airbus Model A330-200 and -300 series airplanes. AD 2011-17-09 required revisions to certain operator maintenance documents to include new inspections. AD 2012-25-12 required replacing certain main landing gear (MLG) bogie beams before reaching new reduced life limits. This new AD requires revising the maintenance or inspection program, as applicable, to incorporate new, more restrictive, or revised instructions and/or airworthiness limitation requirements. This AD was prompted by revisions to certain airworthiness limitation item (ALI) documents, which specify more restrictive instructions and/or airworthiness limitations. We are issuing this AD to address the unsafe condition on these products.
2017-10-04: We are adopting a new airworthiness directive (AD) for all Embraer S.A. Model EMB-120, -120ER, -120FC, -120QC, and -120RT airplanes. This AD was prompted by changes to the airworthiness limitations, which add life-limited landing gear parts not previously identified. This AD requires revising the maintenance or inspection program, as applicable, to incorporate new airworthiness limitations that add life limits for previously unidentified landing gear parts. We are issuing this AD to address the unsafe condition on these products.
72-08-02: 72-08-02 HAWKER SIDDELEY AVIATION: Amdt. 39-1424. Applies to Model DH- 114 "Heron" Series 2 airplanes. Compliance is required as indicated. To prevent failures of the main undercarriage main and damper jack attachment bolts, P/N 14-2U.229 and P/N 14-2U.631, accomplish the following: (a) For airplanes with main undercarriage units that have any P/N 14-2U.229 main and damper jack attachment bolts installed, within the next 150 hours' time in service after the effective date of this AD, unless already accomplished within the last 150 hours' time in service, and thereafter at intervals not to exceed 300 hours' time in service from the last inspection, remove and visually inspect the attachment bolts for cracks. (b) For airplanes with main undercarriage units that have only P/N 14-2U.631 (Modification 1536) main and damper jack attachment bolts installed, within the next 1,200 hours' time in service after the effective date of this AD, unless already accomplished within the last 1,200 hours' time in service, and thereafter at intervals not to exceed 2,400 hours' time in service from the last inspection, remove and visually inspect the attachment bolts for cracks. (c) If any bolt is found to be cracked during an inspection required by paragraph (a) or (b), before further flight replace the cracked bolt in accordance with subparagraph (1) or (2): (1) Replace a cracked bolt, P/N 14-2U.229 with either a serviceable bolt of the same part number or replace with a serviceable bolt, P/N 14-2U.631 (Modification 1536), and continue to inspect in accordance with paragraphs (a) or (b) as applicable. (2) Replace a cracked bolt, P/N 14-2U-631 (Modification 1536), with a serviceable bolt of the same part number and continue to inspect in accordance with paragraphs (a) or (b) as applicable. This amendment becomes effective May 1, 1972.
2024-19-10: The FAA is adopting a new airworthiness directive (AD) for certain Austro Engine GmbH (Austro) Model E4 and E4P engines. This AD was prompted by reports of engine failures and an investigation where cracks were discovered on the pistons. This AD requires repetitive borescope inspections (BSIs) for cracks on the pistons, and, if necessary, removal from service and replacement of the piston, and a fuel sample analysis for water contamination and, if contamination is found, replacement of the high-pressure pump (HPP), injectors, and fuel rails. The FAA is issuing this AD to address the unsafe condition on these products.
2024-16-13: The FAA is adopting a new airworthiness directive (AD) for certain Bombardier, Inc., Model BD-100-1A10 airplanes. This AD was prompted by the discovery of a single-point failure within the left- hand and right-hand heater current monitor (HCM) units. This AD requires installing a monitor circuit comprising relays external to the HCM units. This AD also requires revising the normal and non-normal procedure sections of the existing airplane flight manual (AFM) to add new procedures associated with revised crew alerting system (CAS) messages. The FAA is issuing this AD to address the unsafe condition on these products.
2017-10-02: We are superseding airworthiness directive (AD) 2015-11-01 for Slingsby Aviation Ltd. Models T67M260 and T67M260-T3A airplanes. This AD results from mandatory continuing airworthiness information [[Page 24046]] (MCAI) issued by an aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as failure of a brake master cylinder pivot pin, which could cause the rudder pedal mechanism to detach from the brake cylinder. We are issuing this AD to require actions to address the unsafe condition on these products.
2017-11-02: We are adopting a new airworthiness directive (AD) for all The Boeing Company Model MD-90-30 airplanes. This AD was prompted by a report of cracking in a horizontal stabilizer rear spar cap. This AD requires repetitive inspections for any crack in the left and right side horizontal stabilizer rear spar upper caps, and repair or replacement if necessary. We are issuing this AD to address the unsafe condition on these products.
75-22-08: 75-22-08 SOCIETE NATIONALE INDUSTRIELLE AEROSPATIALE: Amendment 39- 2402. Applies to SA330F and SA330G helicopters certificated in all categories, equipped with external hoists AE-76 360-100 or AE-76 360-110-01. Compliance is required within the next 10 hours' time in service after the effective date of this AD, unless already accomplished. To ensure proper functioning of the pyrotechnic shears, accomplish the following: (a) Inspect electrical connections ME 24F and ME 25F on mobile connector 52 Ma of the pyrotechnic shears control for proper connections. (b) Electrical connections which are improperly connected must be disassembled, reconnected and checked in accordance with paragraph 2.B of Aerospatiale Service Bulletin No. 45.06, dated April 2, 1975, or an FAA-approved equivalent. This amendment becomes effective November 3, 1975.
2017-10-09: We are adopting a new airworthiness directive (AD) for certain Textron Aviation Inc. Models 402C and 414A airplanes (type certificate previously held by Cessna Aircraft Company). This AD requires inspecting the nacelle fittings for cracks, replacing if necessary, and reporting the results of the inspection to the FAA. This AD was prompted by reports of cracks found on certain nacelle fittings. We are issuing this AD to correct the unsafe condition on these products.
2017-09-10: We are adopting a new airworthiness directive (AD) for all The Boeing Company Model 747-400, 747-400D, and 747-400F airplanes. This AD was prompted by a report of a crack in the left wing front spar web, found following a fuel leak. This AD requires repetitive inspections for cracking of the front spar web, and repairs if necessary. We are issuing this AD to address the unsafe condition on these products.
2024-16-10: The FAA is superseding Airworthiness Directive (AD) 2019-25- 17, which applied to all The Boeing Company Model 737-600, -700, -700C, -800, -900, and -900ER series airplanes. AD 2019-25-17 required revising the existing airplane flight manual (AFM) to prohibit selection of certain runways for airplanes equipped with certain software. Since the FAA issued AD 2019-25-17, Boeing has developed new software to address the unsafe condition. This AD was prompted by reports of display electronic unit (DEU) software errors on airplanes with a selected instrument approach to a specific runway. This AD retains the requirements of AD 2019-25-17. This AD also requires installing the new software and performing a software configuration check, which terminates the AFM revision. The FAA is issuing this AD to address the unsafe condition on these products.
74-12-03: 74-12-03 MCDONNELL DOUGLAS: Amendment 39-1858. Applies to DC-8-61F, -62F, -63F convertible freighter airplanes, certificated in all categories. \n\n\t(1)\tFor all aircraft in the passenger configuration, within twenty-four (24) hours of receipt of this telegram, or prior to further flight, whichever occurs later, unless already accomplished within the last 50 hours, perform the passenger oxygen system leak check per paragraph 1(a) DACO Alert Service Bulletin A35-25 Revision A dated May 10, 1974, or later FAA-approved revisions. If the oxygen system does not pass the leak check, inspect, repair and replace worn piping as required, and replace broken and missing supports prior to next flight; repeat leak test per DACO A.S.B. A35-25 Revision A, paragraph 1(a). At intervals not to exceed 50 flight hours visually inspect for worn oxygen piping, replace as necessary, and conduct the leak test per DACO A.S.B. A35-25 Revision A, paragraph 1(a) until the modifications described by DACO A.S.B. A35-25 Revision A, paragraph 1(b) have been accomplished. Within 300 hours time in service after initial leak check, secure all oxygen piping, per DACO A.S.B. A35-25 Revision A, paragraph 1(b). \n\n\t(2)\tFor aircraft in the full freighter configuration, prior to further flight after receipt of this telegram, close the oxygen hand shutoff valve on the passenger system and placard system inoperative until (1), above, is accomplished. Prior to conversion to passenger configuration, perform checks, repair, and modifications of (1) above. Paragraph 2, DACO A.S.B. A35-25 Revision A covers this subject. \n\n\tThis amendment becomes effective June 6, 1974, for all persons except those to whom it was made effective immediately by telegram dated May 11, 1974.