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2024-25-09: The FAA is adopting a new airworthiness directive (AD) for certain The Boeing Company Model 757 airplanes. This AD was prompted by reports of several occurrences of a power transfer unit (PTU) control valve that failed to open when commanded. This AD requires installing new relays and changing certain wire bundles leading to the PTU control valve. The FAA is issuing this AD to address the unsafe condition on these products.
47-02-04: 47-02-04 DOUGLAS: (Was Mandatory Note 12 AD-762-7.) Applies to C-54 and DC-4 Aircraft.\n \n\tTo be accomplished not later than March 15, 1947. \n\n\tRelocate engine primer solenoid to prevent fuel leaking into firewall junction box. This change shall be accomplished in accordance with item 25 of Douglas Service Bulletin C-54-266, dated May 17, 1946, or part 2A, item 4; and part 2C, item 12 of Douglas Service Bulletin DC-4 No. 66, dated June 18, 1947. \n\n\tRevised May 24, 1948.
47-02-09: 47-02-09 CULVER: (Was Mandatory Note 2 of AD-778-2.) Applies to Models V and V2 Aircraft Serial Numbers V-1 to V-150 Inclusive. Compliance required prior to April 1, 1947. Replace the brazed cabin heater valve box mounted on the firewall with a similar welded valve box which has fire resistant properties equivalent to the firewall. (Culver Service Bulletin No. 7 covers this same subject.)
75-17-21: 75-17-21 HAWKER SIDDELEY AVIATION, LTD: Amendment 39-2323. Applies to DH-125 and BH-125 airplanes certificated in all categories. Compliance required as indicated. To prevent possible rapid loss of cabin pressurization, accomplish the following: Within 50 hours time in service after the effective date of this AD, unless already accomplished, inspect all Hellerman type cabin pressure seal bungs for displacement and rework as necessary in accordance with the following: (a) Locate all Hellerman type cabin pressure seal bungs for the particular aircraft being inspected. NOTE: Refer to the relevant aircraft wiring diagram manual (2 volumes) and to the maintenance practices in the Maintenance Manual, Chapter 24-00 (all series pre-600) and Chapter 24-01 (series 600). Pressure bung installations may be of the normal or reverse type assembly as defined in the Maintenance Manual reference noted in paragraph (c) of this AD. The total number may vary from one airplane toanother depending on the electrical equipment installed. (b) Gain access to the bungs in accordance with the procedures in the Maintenance Manual, Chapters 24 and 25. (c) Inspect the bungs (both normal and reverse assemblies) for displacement and reinspect and/or rework as necessary in accordance with the instructions contained in Part B of temporary revision dated April 1, 1975, to HSA Maintenance Manual, Chapter 24-00 (all series except 600) and Chapter 24-01 (series 600), or the appropriate sections of the referenced chapters if the temporary revision has been incorporated into the HSA Maintenance Manual, or an FAA-approved equivalent. (d) Where pressure bung(s) have been removed for rework, upon re-installation of the pressure bung(s) conduct a cabin leak rate check in accordance with the appropriate provisions of chapter 21 of the HSA Maintenance Manual prior to further flight to ensure the integrity of the pressure cabin. This amendment becomes effective August 19, 1975.
2016-01-19: We are adopting a new airworthiness directive (AD) for MD Helicopters Inc. (MDHI) Model 500N and 600N helicopters with certain rotating cone assemblies installed. This AD requires establishing a life limit of 10,000 hours time-in-service (TIS) on these rotating cone assemblies. This AD was prompted by the determination that MDHI created rotating cone assemblies with new dash numbers but incorrectly failed to identify them as life-limited parts. The actions are intended to prevent operation of rotating cone assemblies past their life limits, failure of the rotating cone assemblies, loss of directional control, and subsequent loss of control of the helicopter.
86-19-07: 86-19-07 BOEING: Amendment 39-5402. Applies to all Model 767 airplanes, certificated in any category, listed in Boeing Service Bulletin 767-52-0042, Revision A, dated January 15, 1986. To prevent structural failure of the vertical fin in the event of a rupture of the aft pressure bulkhead, accomplish the following within 12 months after the effective date of this amendment, unless already accomplished: \n\n\tA.\tInstall a stronger replacement fin access door or reinforce the existing fin access door in accordance with Boeing Service Bulletin 767-52-0042, Revision A, dated January 15, 1986, or later FAA-approved revisions. \n\n\tB.\tAlternate means of compliance or adjustment of compliance times, which provide an acceptable level of safety, may be used when approved by the Manager, Seattle Aircraft Certification Office, FAA, Northwest Mountain Region. \n\n\tAll persons affected by this directive who have not already received the appropriate service document from the manufacturer, may obtain copies upon request to the Boeing Commercial Airplane Company, P.O. Box 3707, Seattle, Washington 98124-2207. This document may be examined at the FAA, Northwest Mountain Region, 17900 Pacific Highway South, Seattle, Washington, or the Seattle Aircraft Certification Office, 9010 East Marginal Way South, Seattle, Washington. \n\n\tThis amendment becomes effective October 2, 1986.
86-02-52 R1: 86-02-52 R1 PRATT & WHITNEY: Amendment 39-5264. Applies to Pratt & Whitney (PW) JT8D-1, -1A, -1B, -7, -7A, -7B, -9, -9A, -11, -15, -15A, -17, -17A, -17R, and -17AR model turbofan engines overhauled by Aerothrust Corporation of Miami, Florida, with the following serial numbers: 648779 654034 657429 667109 688132 649019 654072 657480 667127 688418 649218 654344 657591 667130 688440 649255 654595 657699 667144 688441 649281 654799 657714 667203 688444 649283 654806 657742 667204 688445 649285 654857 665873 667216 688473 649347 654909 666661 674268 688504 649581 654975 666685 674465 688505 649655 655366 666716 674564 688509 653453 655813 666738 674611 688839 653509 655920 666764 687309 688844 653512 655967 666804 687323 689877 653526 656047 666850 687413 689935 653571 656089 666853 687715 696688 653645 656120 666878 687727 696720 653699 656854 666976 687806 702937 653838 656975666980 687836 702938 653854 657066 666989 687840 702975 653992 657112 666993 687841 653996 657201 667042 657258 667059 Compliance is required as indicated unless already accomplished. To prevent fracture of the combustion chamber which could result in an uncontained engine failure, accomplish the following: NOTES: 1) For the initial inspection, time since inspection (TSI) is defined as hours or cycles since installation by Aerothrust. Thereafter, for the repetitive inspections, TSI is defined as hours or cycles since the last inspection. 2) For the initial inspection, the cumulative crack length at the 2-3 seam weld is that present at the time of installation by Aerothrust as determined by individual chamber x-ray film records on file at Aerothrust. 3) Investigation is continuing and pending the results, additional engine serial numbers may be added to this AD. (a) Remove from service within the next 100 hours or 100cycles time in service from the effective date of this AD, whichever occurs first, chambers with greater than 8 inches but less than or equal to 12 inches cumulative crack length at installation by Aerothrust. (b) Remove from service, prior to further flight, chambers with greater than 12 inches cumulative crack length at installation by Aerothrust. (c) Inspect combustion chamber 2-3 seam welds in accordance with PW Service Bulletin Number 5639, dated November 15, 1985, or FAA approved equivalent, per the following schedule: (1) Inspect chambers with 3 inches or less cumulative crack length as follows: (i) Prior to accumulating 2,000 hours or 1,500 cycles TSI, whichever occurs first; or (ii) For chambers with greater than 1,900 hours or 1,400 cycles TSI on the effective date of this AD, inspect within the next 100 hours or 100 cycles time in service, whichever occurs first. (2) Inspect chambers with greater than 3 inches but less than or equal to 6 inches cumulative crack length as follows: (i) Prior to accumulating 1,500 hours or 1,000 cycles TSI, whichever occurs first; or (ii) For chambers with greater than 1,400 hours or 900 cycles TSI on the effective date of this AD, inspect within the next 100 hours or 100 cycles time in service, whichever occurs first. (3) Inspect chambers with greater than 6 inches but less than or equal to 8 inches cumulative crack length as follows: (i) Prior to accumulating 250 hours or 200 cycles TSI, whichever occurs first; or (ii) For chambers with greater than 150 hours or 100 cycles TSI on the effective date of this AD, inspect within the next 100 hours or 100 cycles time in service, whichever occurs first. (4) Chambers for which the cumulative crack length at installation by Aerothrust cannot be confirmed must be inspected within the next 100 hours or 100 cycles time in service, whichever occurs first. (d) Reinspect chambers, thereafter, in accordancewith the appropriate inspection interval of paragraphs (c)(1) through (c(3), as determined by the crack length at last inspection or at installation by Aerothrust, whichever crack length is greater. Remove from service, prior to further flight, any chambers with greater than 8 inches cumulative crack length at reinspection. Aircraft may be ferried in accordance with the provisions of FAR 21.197 and 21.199 to a base where the AD can be accomplished. Upon request, an equivalent means of compliance with the requirements of this AD may be approved by the Manager, Engine Certification Office, New England Region. Upon submission of substantiating data by an owner or operator through an FAA maintenance inspector, the Manager, Engine Certification Office, New England Region, may adjust the compliance time specified in this AD. Pratt & Whitney Service Bulletin Number 5639, dated November 15, 1985, identified and described in this document 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 Pratt & Whitney, East Hartford, Connecticut. This document may also be examined at the Office of the Regional Counsel, Federal Aviation Administration, Rules Docket Number 86-ANE-3, 12 New England Executive Park, Burlington, Massachusetts 01803, weekdays, except Federal holidays, between 8:00 a.m. and 4:30 p.m. This amendment becomes effective April 14, 1986, as to all persons except those persons to whom it was made immediately effective by TAD T86-02-52, issued January 29, 1986, which contained this amendment. TAD T86-02-52 superseded TAD T85-17-51R1 for the engines affected by this TAD, and this TAD supersedes TAD T86-02-51.
93-16-15: 93-16-15 TELEDYNE CONTINENTAL MOTORS: Amendment 39-8743. Docket 93-ANE-55. Applicability: Teledyne Continental Motors (TCM) Model IO-520B, IO-520BA, IO-520BB, IO-520C, IO- 520CB, IO-520M, IO-520MB; IO-550A, IO-550B, IO-550C, IO-550G; TSIO-520B, TSIO-520BB, TSIO-520D, TSIO-520DB, TSIO-520E, TSIO-520EB, TSIO-520J, TSIO-520JB, TSIO-520K, TSIO-520KB, TSIO-520L, TSIO-520LB, TSIO-520N, TSIO-520NB, TSIO-520UB, TSIO-520VB, TSIO-520WB; TSIO-550B; and TSIOL- 550A and TSIOL-550B reciprocating engines, with serial numbers lower than those listed in TCM Mandatory Service Bulletin (MSB) No. M93-9, Revision 1, dated March 10, 1993; which are equipped with the following fuel pumps: Part Numbers (P/N) 646210-1, -2, -8, -10, -11; P/N 646212-2, -5, -16, -17; P/N 646758-5, -7, -8, -9; P/N 646765-6 and -7; P/N 646766-1 and -2; 646767-1; 649368-19; or engines equipped with any fuel pump, regardless of part number that have had the fuel pump replaced in the field prior to the effective date of this AD with fuel pump drive shaft, P/N 646176, installed. These engines are installed on but not limited to the following aircraft: Beech Bonanza 35-C33A, E33A/C, F33A/C, S35, V35/A/B, A36/TC, B36TC; Beech Baron 95-C55/A, D55/A, E55/A, 58/A/P/PA/TC/TCA; Cessna 310R, T310P/Q/R, 320 D/E/F, 335 series, 340 series, 401 series, 402 series, 414 series; Cirrus VK-30; Lancaire IV; Mooney M20K with Rocket Engineering Corporation "Rocket Mooney" STC; Navion Model H; and Questair. Compliance: Required as indicated, unless accomplished previously. To prevent possible fuel pump drive shaft disengagement and loss of engine power, accomplish the following: (a) Within the next 30 hours time in service after the effective date of this AD, visually inspect the fuel pump to determine which combination of fuel pump drive shaft and fuel pump drive coupling is installed, and replace, if necessary, fuel pump drive couplings that have less than the minimum required coupling engagement with longer fuelpump drive couplings, in accordance with Figure 1 of TCM MSB No. M93-9, Revision 1, dated March 10, 1993, as follows: (1) If fuel pump drive shaft, P/N 646176, is installed with fuel pump drive coupling, P/N 631263, replace the fuel pump drive coupling with a serviceable fuel pump drive coupling, P/N 653359. (2) If fuel pump drive shaft, P/N 643689, is installed with either fuel pump drive coupling, P/N 631263 or 653359, no further action is required. (3) If fuel pump drive shaft, P/N 646176, is installed with fuel pump drive coupling, P/N 653359, no further action is required. (b) 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, Atlanta Aircraft Certification Office. The request should be forwarded through an appropriate FAA Maintenance Inspector, who may add comments and then send it to the Manager, Atlanta Aircraft Certification Office. NOTE: Information concerning the existence of approved alternative methods of compliance with this airworthiness directive, if any, may be obtained from the Atlanta Aircraft Certification Office. (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 inspections, and replacement, if necessary, shall be done in accordance with the following service bulletin: Document No. Pages Revision Date TCM MSB No. M93-9 1-5 1 March 10, 1993 Total pages: 5. 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 Teledyne Continental Motors, P.O. Box 90, Mobile, AL 36601; telephone (205) 438-3411. 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. (e) This amendment becomes effective December 14, 1993, to all persons except those persons to whom it was made immediately effective by priority letter AD 93-16-15, issued September 27, 1993, which contained the requirements of this amendment.
2024-25-04: The FAA is superseding Airworthiness Directive (AD) 2023-23- 10, which applied to all Embraer S.A. Model ERJ 190-300 airplanes. AD 2023-23-10 required repetitive inspections of the press-fitted bushings of the wing ailerons for migration and broken sealant, measurements of the distance between the aileron surfaces and hinge fittings, functional checks of the backlash of the wing aileron control system, and all applicable related investigative and corrective actions. Since the FAA issued AD 2023-23-10, it was determined that certain requirements needed to be clarified. This AD continues to require all actions of ANAC AD 2023-06-01 with revised compliance requirements, 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.
85-01-03: 85-01-03 McDONNELL DOUGLAS: Amendment 39-4977. Applies to McDonnell Douglas Model DC-9 and C-9 (Military) series airplanes, manufacturer's fuselage numbers 1 through 1125, certificated in all categories. Compliance required as indicated, unless previously accomplished. \n\n\tTo prevent failures of the spoiler drive link(s), P/N 3923250-1, -501 and/or -503; and spoiler fitting(s), P/N 3923251-1 and/or -501, accomplish the following: Part I \n\n\tA.\tApplies to McDonnell Douglas DC-9-10 through -50, and C-9 (Military) series airplanes. \n\n\t\t1.\tFor operators who have accomplished terminating action in accordance with Airworthiness Directive (AD) 74-16-02, Amendment 39-2213, dated May 27, 1975, within the next 3,000 flight hours or 3,000 cycles, whichever occurs first, from the effective date of this AD, and thereafter at intervals not to exceed 3,000 flight hours or 3,000 cycles, whichever occurs first, perform non-destructive inspection (NDI) in accordance with the instructions contained in McDonnell Douglas Non-Destructive Testing (NDT) Manual, TR 7-1 through 7-4, referenced in McDonnell Douglas DC-9 Service Bulletins 27-228 and/or 27-229, both service bulletins dated August 19, 1982, or later NDT Manual or Service Bulletin revisions approved by the Manager, Los Angeles Aircraft Certification Office, FAA, Northwest Mountain Region. Alternate means of compliance which provide an equivalent level of safety may be used when approved by the Manager, Los Angeles Aircraft Certification Office, FAA, Northwest Mountain Region. \n\n\tNOTE: McDonnell Douglas Service Bulletins 27-228 and 27-229, both dated August 19, 1982, and 27-240, dated June 30, 1983, are hereinafter referred to as SB 27-228, SB 27-229, and SB 27-240. \n\n\t\t2.\tFor operators who have instituted the program of visual/repetitive inspections in accordance with AD 74-16-02, Amendment 39-2213, dated May 27, 1975, at the next scheduled repetitive inspection, comply with the instructions in accordance with this AD, as applicable. \n\n\t\t3.\tFor operators who have not implemented AD 74-16-02, Amendment 39-2213, dated May 27, 1975: \n\n\t\t\ta.\tWithin the next 300 flight hours or 300 cycles, whichever occurs first, and thereafter at intervals not to exceed 300 flight hours or 300 cycles from the effective date of this AD: \n\n\t\t\t\t(1)\tVisually inspect the exposed surfaces on the forward and aft lugs, including the areas surrounding the grease fittings on the spoiler actuating link, and \n\n\t\t\t\t(2)\tVisually inspect the exposed surface and areas surrounding the grease fitting on the spoiler fitting. \n\n\t\t\tb.\tAt or prior to the accumulation of an additional 1,000 flight hours or 1,000 cycles, whichever comes first, from first visual inspection on these parts, and thereafter at intervals not to exceed 3,000 flight hours or 3,000 cycles, whichever comes first, institute the program of NDI inspections as required by Part I, paragraph A.1, above, until terminating action in accordance with Part I, Paragraph A.6., below, is accomplished. \n\n\t\t\tNOTE: The requirements for visual inspections may be terminated upon instituting the NDI program specified in Part I, paragraph A.1, of this AD. \n\n\t\t4.\tIf no cracks are found in the spoiler drive link or fitting assemblies in the areas identified by Figures 1 through 7 of NDT Manual TR 7-1 through TR 7-4 referenced in SB 27-228 and/or SB 27-229, or a FAA approved alternate NDT method in accordance with Part I, paragraph C.3., below, continue repetitive inspections in accordance with Part I, paragraph A.1., above, until such time terminating action is accomplished in accordance with Part I, paragraph A.6., below. \n\n\t\t5.\tIf cracks are found in the spoiler drive links, or fittings in areas identified by Part I, paragraph A.3., above. \n\n\t\t\ta.\tReplace with new flight spoiler components, in accordance with paragraph 2. of the Accomplishment Instructions, Figure 1, of SB 27-240. \n\n\t\t\tb.\tReplace with spoiler drive link, or aft attach fitting, and continue repetitive inspection in accordance with Part I, paragraph A.1., above, until terminating action is accomplished in accordance with Part I, paragraph A.6., below. \n\n\t\t6.\tReplacement of the flight spoiler components with new components in accordance with SB 27-240, dated June 30, 1983, or later FAA approved revisions, constitutes terminating action for repetitive inspection requirements of this AD. \n\n\t\tNOTE: Accomplishment of the preventive modification in accordance with SB 27-240 will constitute terminating action for the repetitive inspection requirements of this AD. \n\n\tB.\tApplies to McDonnell Douglas DC-9-80 series airplanes: \n\n\t\t1.\tAirplanes that are not affected by AD 74-16-02, Amendment 39-2213, dated May 27, 1975, but are affected by McDonnell Douglas Report MDC-J8855, Revisions A through G, or later FAA approved revisions, will continue existing inspection program. This program performs NDT inspections of the flight spoiler drive links or fittings, as follows: \n\n\t\t\ta.\tOne time visual inspection prior to exceeding 5000 total airplane flight hours. \n\n\t\t\tb.\tInitial ultrasonic and/or eddy current inspection within 1000 flight hours after visual inspection. \n\n\t\t\tc.\tRepetitive ultrasonic and/or eddy current inspections at intervals not to exceed 3000 flight hours or 3000 landings whichever occurs first, until Service Bulletin 27-240 is accomplished. \n\n\t\t\td.\tReplacement of flight spoiler drive link with a new P/N 3923250-503 link requires reinstituting the repetitive ultrasonic and/or eddy current inspections within 6000 flight hours or 6000 landings, whichever occurs first. \n\n\t\t\te.\tReplacement of flight spoiler drive fitting with new P/N 3923251-1 "G" or -501 fitting assembly requires reinstituting the repetitive ultrasonic and/or eddy current inspections within 6000 flight hours or 6000 landings, whichever comes first. \n\n\t\t2.\tAccomplishment of the preventative modifications in accordance with SB 27-240 will constitute terminatingaction for the special inspection requirements listed in McDonnell Douglas Report MDC-J8855, Parts III and IV, Revisions A through G, or later FAA approved revisions. \n\n\tC.\tApplies to all McDonnell Douglas DC-9 and Military C-9 series airplanes: \n\n\t\t1.\tSpecial flight permits may be issued in accordance with Federal Aviation Regulations (FAR) 21.197 and 21.199 to operate airplanes to a base for the accomplishment of modifications required by this AD. \n\n\t\t2.\tUpon the request of an operator, an FAA Maintenance Inspector, subject to approval by the Manager, Los Angeles Aircraft Certification Office, FAA, Northwest Mountain Region, may adjust the repetitive inspection intervals specified in this AD to permit compliance at an established inspection period of that operator, if the request contains substantiating data to justify the change for that operator. \n\n\t\t3.\tAlternate means of compliance which provide an equivalent level of safety may be used when approved by the Manager, Los Angeles Aircraft Certification Office, FAA, Northwest Mountain Region. \n\n\t\tNOTE: For purposes of this AD, if the time-in-service hours of either the spoiler actuating link or the spoiler fitting cannot be established, the part will be considered to have the same number of time-in-service hours as the airplane on which it is installed. \n\nPart II \n\n\tApplies to all DC-9 series aircraft, fuselage numbers 1 through 1125, certificated in all categories, as indicated below: \n\n\tTo provide crews with operation information should spoiler float occur, evidenced by abrupt roll, and to provide for a permanent change in the "Emergency Procedures" Section of the FAA approved Airplane Flight Manual (AFM) (and appropriate AFM sections of the operator's manual required by FAR 121.133 and 121.141), accomplish the following: \n\n\tA.\tPLACARD \n\n\tWithin 30 days after effective date of this AD, unless already accomplished, install a placard as close as practicable to the flap position indicator, containing the following wording or an equivalent wording as approved by the Manager, Los Angeles Aircraft Certification Office, FAA, Northwest Mountain Region, reading as follows: \n\n\tDC-9-10 \n\n\t"Flap selection excess 20 degrees must be made prior to 1000 feet AGL. See Section I, AFM for alternate procedures." (The last sentence may be omitted from the placard if the use of alternate landing flap setting is not desired.) \n\n\tDC-9-20, -30, -40, -50, and C-9 (Military Series) \n\n\t"Flap selection excess 25 degrees must be made prior to 1000 feet AGL. See Section I, AFM for alternate procedures." (The last sentence may be omitted from the placard if the use of alternate landing flap setting is not desired.) \n\n\tDC-980 Series \n\n\t"Flap selection excess 28 degrees must be made prior to 1000 feet AGL. See Section I, AFM for alternate procedures." (The last sentence may be omitted from placard if the use of alternate landing flap setting is not desired.) \n\n\tB.\tLIMITATIONS \n\n\t\t1.\tThe limitations set forth below are effective as of June 14, 1974, for the Models DC-9-10 through -40 series and C-9A and C-9B airplanes; and effective within 30 days after the effective date for the Models DC-9-50 and -80 series airplanes. \n\n\t\t2.\tWithin 30 days after the effective date of this AD, unless already accomplished, incorporate the "Limitations" set forth below into the Airplane Flight Manual (AFM). Operators must initiate actions to notify and ensure that the flight crewmembers are apprised of these limitations. \n\n\tDC-9-10 Series \n\n\tSec. I Limitations: (New Title) "Flaps": \n\n\t"Flap selection in excess of 20 degrees must be made prior to descending below 1000 feet above ground level except for the following: \n\n\tApproach and landing may be made with a maximum of 30 degree flap when 15 percent is added to the 50 degree flap landing field length." \n\n\tSec. I Limitations: Performance and Operating Limitations. Add a new paragraph as follows: \n\n\t"When using the 30 degrees flaps for landing, the maximum permissible quick turn around landing weight shown on the plot 'Maximum Permissible Quick Turn Around Landing Weight Flaps Down' in Section IV must be reduced by 15 percent." \n\n\tDC-9-20, -30, -40, -50, and C-9 (Military Series) \n\n\tSec. I Limitations: (New Title) "Flaps" \n\n\t"Flap selection in excess of 25 degrees must be made prior to descending below 1000 feet above ground level except for the following: \n\n\tApproach and landing may be made with a maximum of 25 degree flap when 20 percent is added to the 50 degree flap landing field length." \n\n\tSec. I Limitations: Performance and Operating Limitations. Add new paragraph as follows: \n\n\t"When using the 25 degree flap for landing, the maximum permissible quick turn around landing weight shown on the plot 'Maximum Permissible Quick Turn Around Landing Weight Flaps Full Down' in Section IV must be reduced by 20 percent." \n\n\tDC-9-80 Series \n\n\tSec. I Limitations: "Flaps" \n\n\t"Flap selection in excess of 28 degrees must be made prior to descending below 1000 feet above ground level." \n\n\t\t3.\tThe above "Limitations" may be terminated, and the "Placard" removed when operator(s) have implemented the repetitive inspections required by Part I of this AD. \n\n\tC.\tEMERGENCY PROCEDURES \n\n\t\t1.\tThe Emergency Procedures set forth below are effective as of June 14, 1974, for the Models DC-9-10 through -40 series and C-9A and C-9B airplanes; and effective within 30 days after the effective date of this AD for the Models DC-9-50 and -80 series airplanes. \n\n\t\t2.\tWithin 30 days after the effective date of this AD, unless already accomplished, incorporate the "Emergency Procedures" set forth below into the Airplane Flight Manual. These procedures constitute a permanent change to the manual. Operators must initiate action to notify and ensure that flight crewmembers are apprised of this change. \n\n\tDC-9-10, -20, -30, -33F, -40, and C-9 (Military Series) \n\n\tSection II: Emergency Procedure (New Title) "Spoiler Float"; \n\n\t"Should rapid roll develop during extension of flap to 50 degrees, retract immediately to single engine landing flap setting. Adjust speed as required." \n\n\tDC-9-34, -50 Series \n\n\tSection II: Emergency Procedure (New Title) "Spoiler Float"; \n\n\t"Should rapid roll develop during extension of flap beyond 25 degrees, retract immediately to single engine landing flap setting. Adjust speed as required." \n\n\tDC-9-80 Series \n\n\tSection II: Emergency Procedure (New Title) "Spoiler Float"; \n\n\t"Should rapid roll develop during extension of flap beyond 28 degrees, retract immediately to single engine landing flap setting. Adjust speed as required." \n\n\tAll persons affected by this directive who have not already received these documents 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 also 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\tThis supersedes AD 74-16-02, Amendment 39-2213, dated May 27, 1975. \n\n\tThis amendment becomes effective February 14, 1985.
2021-09-11: The FAA is adopting a new airworthiness directive (AD) for all Saab AB, Support and Services Model SAAB 2000 airplanes. This AD was prompted by a report indicating that the left-hand main landing gear (MLG) collapsed after touchdown, causing severe damage to the airplane. This AD requires modifying the MLG hydraulic transfer valve, as specified in a European Union Aviation Safety Agency (EASA) AD, which is incorporated by reference. The FAA is issuing this AD to address the unsafe condition on these products.
91-15-15: 91-15-15 E.I. DUPONT DE NEMOURS & COMPANY: Amendment 39-7079. Docket No. 91-ANE-21. Applicability: E.I. DuPont de Nemours & Co., TSO-C116 Crewmember Protective Breathing Equipment Model 4566M37B-042N, with serial numbers below S/N V9100000, installed on, but not limited to transport category aircraft. Compliance: Required as indicated, unless previously accomplished. To prevent the failure of a crewmember to remove the pouch from the bracket in case of a fire, accomplish the following within 45 days after the effective date of this AD: (a) Remove the Velcro Strips and insert new left and right spacers in accordance with Paragraph 2, Procedure Instructions, of E.I. DuPont de Nemours & Co., Service Bulletin 002, dated February 5, 1991. (b) Aircraft may be ferried in accordance with the provisions of FAR 21.197 and 21.199 to a base where the AD can be accomplished. (c) Upon submission of substantiating data by an owner or operator through an FAA Inspector (maintenance, avionics, or operations, as appropriate), and alternate method of compliance with the requirements of this AD or adjustments to the compliance specified in this AD may be approved by the Manager, New York Aircraft Certification Office, 181 South Franklin Ave., Valley Stream, New York, 11581-1145. (d) The modifications shall be done in accordance with the following E.I. DuPont de Nemours & Co. Service Bulletin No. 002: Page No. Issue Date 1-5 Original February 5, 1991 Total Pages: 5 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 E.I. Dupont de Nemours & Co., P.O. Box 791, 505 Blue Ball Road, Elkton, Maryland 21921. Copies may be inspected at the FAA, New England Region, Office of the Assistant Chief Counsel, Room 311, 12 New England Executive Park, Burlington, Massachusetts, or New York Aircraft Certification Office, 181South Franklin Ave., Valley Stream, New York, or at the Office of the Federal Register, 1100 L Street, NW, Room 8401, Washington, D.C. Airworthiness Directive 91-15-15, published in the Federal Register on July 26, 1991, was not distributed to the public by FAA due to a clerical error in the AD. This corrected version of AD 91-15-15, Amendment 39-7079, published in the Federal Register on August 15, 1991, becomes effective on August 15, 1991.
2003-16-09: This amendment adopts a new airworthiness directive (AD) that is applicable to certain Learjet Model 45 airplanes. This action incorporates a reduced life-limit replacement interval for certain shear pins in the trunnion assemblies of the main landing gears (MLG) into the airworthiness limitations section of the Instructions for Continued Airworthiness, and requires replacement of those certain shear pins with new, improved shear pins. This action is necessary to prevent failure of the shear pins in the trunnion assemblies of the MLGs, which could result in the collapse of a MLG, and consequent reduced controllability of the airplane during takeoff or landing. This action is intended to address the identified unsafe condition.
2002-24-08: This amendment supersedes Airworthiness Directive (AD) 2002- 05-05, which currently applies to certain Cirrus Design Corporation (Cirrus) Models SR20 and SR22 airplanes. AD 2002-05-05 currently requires you to incorporate temporary operating limitations into the Limitation Section of the airplane flight manual (AFM) for certain affected airplanes and install a cable clamp external to the cone adapter on the Cirrus Airplane Parachute System (CAPS) activation cable for all affected airplanes. AD 2002-05-05 resulted from a report from the manufacturer that certain CAPS may not activate in an emergency situation. This AD is the result of the manufacturer redesigning the CAPS activation system. This AD requires you to modify the CAPS activation system. The actions specified by this AD are intended to prevent failure of the CAPS activation system in an emergency situation. Failure of this system could result in occupant injury and/ or loss of life and loss of aircraft.
2002-24-07: This amendment adopts a new airworthiness directive (AD) that applies to certain Aerostar Aircraft Corporation (Aerostar) Models PA- 60-601 (Aerostar 601), PA-60-601P (Aerostar 601P), PA-60-602P (Aerostar 602P), and PA-60-700P (Aerostar 700P). This AD requires you to replace Roto-Master and Rajay scavenge pumps with improved design Aerostar scavenge pumps. This AD is the result of failures of the existing Roto- Master and Rajay scavenge pumps found during regular maintenance inspections. The actions specified by this AD are intended to prevent in-flight failure of the oil scavenge pumps, which could result in loss of engine oil and possible loss of engine power.
2002-23-19: This amendment supersedes an existing airworthiness directive (AD), applicable to all Dassault Model Falcon 2000 series airplanes, and certain Dassault Model Falcon 900EX and Mystere Falcon 900 series airplanes. That AD currently requires repetitive operational tests of the flap asymmetry detection system to verify proper functioning, and repair, if necessary; repetitive replacement of the inboard flap jackscrews with new or reconditioned jackscrews; and repetitive measurement of the screw/nut play of the jackscrews on the inboard and outboard flaps to detect discrepancies, and corrective action if necessary. This amendment removes Model 900EX and Mystere Falcon 900 series airplanes from the applicability of the existing AD. For Model Falcon 2000 series airplanes, this amendment also adds certain repetitive measurements, deletes certain repetitive measurements, and extends the interval for repetitive replacement of certain jackscrews. This amendment is prompted by issuance ofmandatory continuing airworthiness information by a foreign civil airworthiness authority. The actions specified by this AD are intended to prevent jamming of the flap jackscrews during the approach to landing, which could result in inability to move the flaps or an asymmetric flap condition, and consequent reduced controllability of the airplane.
90-01-11: 90-01-11 BELL HELICOPTER TEXTRON, INC.: Amendment 39-6450. Docket No. 89-ASW-50. Applicability: Bell Helicopter Textron, Inc., Model 204B helicopters, certificated in any category, with tail rotor gearbox duplex bearing sets, P/N 204-040-424-001, with serial numbers (S/N's) 1 thru 182, MB183 thru MB382, MB442, MB486, MB513, MB518, MB519, MB524, MB530, MB531, MB544, MB545, MB548, MB549, MB551, MB553, MB554, MB561, MB659, MB743, MB744, MB760 thru MB769 and MB927 thru MB936, installed in tail rotor gearbox output quill, P/N 204-040-012-009. Compliance: Required as indicated, unless already accomplished. To prevent failure of the tail rotor duplex bearing which could result in loss of tail rotor control and subsequent loss of the helicopter, accomplish the following: (a) Within the next 100 hours' time in service after the effective date of this AD, remove the tail rotor gearbox duplex bearing set, P/N 204-040-424-001, from service and replace with a serviceablepart before further flight. (b) In accordance with FAR Sections 21.197 and 21.199, the helicopter may be flown to a base where the requirements of this AD may be accomplished. (c) An alternate method of compliance or adjustment of the compliance time which provides an acceptable level of safety may be used when approved by the Manager, Rotorcraft Certification Office, ASW-170, Rotorcraft Directorate, FAA, Southwest Region, Fort Worth, Texas. This amendment (39-6450, AD 90-01-11) becomes effective on February 1, 1990.
2024-25-01: The FAA is superseding Airworthiness Directive (AD) 2023-23- 09, which applied to all Embraer S.A. Model ERJ 190-400 airplanes. AD 2023-23-09 required repetitive inspections of the press-fitted bushings of the wing ailerons for migration and broken sealant, measurements of the distance between the aileron surfaces and hinge fittings, functional checks of the backlash of the wing aileron control system, and all applicable related investigative and corrective actions. Since the FAA issued AD 2023-23-09, it was determined that certain requirements needed to be clarified. This AD continues to require all actions of ANAC AD 2023-05-02 with revised compliance requirements, 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.
2016-01-09: We are adopting a new airworthiness directive (AD) for certain Bombardier Model DHC-8-400 series airplanes. This AD was prompted by a report of several cracks found on the forward passenger airstair door step assembly. This AD requires an inspection to determine the serial number of the airstair door step assembly, and if necessary, an electronic tap test, reidentification of the airstair door step assembly, and replacement of the airstair door step assembly. We are issuing this AD to detect and correct cracks in the forward passenger airstair door step assembly; such cracking could propagate and result in the structural failure of the steps and impede the evacuation of passengers in the event of an emergency egress situation.
84-21-01 R1: 84-21-01 R1 BRITISH AEROSPACE: Amendment 39-4932 as amended by Amendment 39- 4993. Applies to all Model DH/HS/BH 125 series airplanes certificated in all categories, with the serial numbers specified in the service bulletins listed below. Compliance is required as indicated. To prevent electrical failures in the 'ZL' panel, accomplish the following within the next 90 days after the effective date of this AD unless previously accomplished: A. Replace the two existing 80 amp fuses on the 'ZL' panel with 100 amp fuses, in accordance with the Accomplishment Instructions of British Aerospace 125 Aircraft Service Bulletin 24-239-(2885), Revision 1, dated February 27, 1984. B. Install covers on the 'ZL' panel as follows: 1. For aircraft that have accomplished STC SA3870WE or STC SA3925WE, in accordance with the Accomplishment Instructions of AiResearch Aviation Company Service Bulletin No. 6-7, dated October 25, 1983. 2. For any other aircraft fitted with Garrett TFE 731-3 engines, in accordance with the Accomplishment Instructions of British Aerospace 125 Aircraft Service Bulletin 24-220-(2749), Revision 3, dated March 3, 1983. C. Alternate means of compliance which provide an equivalent level of safety may be used when approved by the Manager, Seattle Aircraft Certification Office, FAA, Northwest Mountain Region. D. Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate airplanes to a base for the accomplishment of inspections and/or modifications required by this AD. Amendment 39-4932 became effective November 14, 1984. This Amendment 39-4993 becomes effective February 11, 1985.
59-18-02: 59-18-02 BEECH: Applies to All Model C45G, TC45G, C45H, TC45H and D18S Airplanes. Compliance required as indicated. Corrosion of fuel supply lines in the wing root area can result from the flexible cockpit hot air duct touching the aluminum fuel line. Fuel line leaks due to this corrosion may cause fuel system malfunctioning or hazardous accumulations of fuel and fumes in the wings or cabin. To prevent these conditions, accomplish the following: (a) Compliance required not later than October 15, 1959. (1) Inspect the 5/8-inch O.D. fuel line (Beech P/N's 407-189686 LH and 407-189731 RH) beneath each battery installation on both sides of the airplane for indications of corrosion. Replace the lines if damaged. (2) Install 5/8-inch I.D. x 1/16-inch tubing (Tygon tubing manufactured by U.S. Stoneware, Akron 9, Ohio) split lengthwise over the fuel lines (407-189686 LH and 407- 189731 RH) in the area of the cockpit hot air duct. Secure the split tubing by taping. (3) Obtain adequate clearance between the fuel line and the cabin hot air duct by installing a suitable double clamp on the line and duct. (b) Compliance required at each periodic airplane inspection after accomplishment of (a). (1) Remove split Tygon tubing from fuel supply lines (407-189686 LH and 407-189731 RH) and inspect lines for corrosion. Replace fuel lines if necessary. (2) Reinstall split Tygon tubing and double clamp between cabin hot air duct and fuel line as outlined in (a)(2) and (a)(3). (Beech Service Bulletin No. 68, Model D18S issued February 1959, covers this same subject.)
67-25-01 R1: 67-25-01 R1 BRITISH AIRCRAFT: Amendment 39-476 as amended by 39-4217. Applies to Model BAC 1-11 200 and 400 Series Airplanes. Compliance required as indicated To prevent fatigue failures of the Belleville washers installed in the main undercarriage down lock jacks P/N AB43A15 and AB43A16 (200 Series), P/N AK43A15 and AK43A16 (400 Series), accomplish the following: (a) For airplanes with Belleville washers P/N 1383 No. 12 (Terry) installed in the main undercarriage down lock jacks with less than 4,760 landings on the effective date of this AD, inspect the main undercarriage down lock links P/N AB43A17 (200 Series) or P/N AK43A17 (400 Series) before the accumulation of 5,000 landings, and thereafter at intervals not to exceed 240 landings from the last inspection in accordance with British Aircraft Corporation, BAC 1-11 Alert Service Bulletin 32-A-PM 2437, Issue 3, dated February 1, 1967, or later ARB- approved issue. Replace cracked or broken washers, and remove washersfrom service before the accumulation of 8,000 landings. (b) For airplanes with Belleville washers P/N 1383 No. 12 (Terry) installed in the main undercarriage down lock jacks with 4,760 or more landings but less than 7,760 landings on the effective date of this AD, inspect the main undercarriage down lock links P/N AB43A17 (200 Series) or P/N AK43A17 (400 Series) within the next 240 landings after the effective date of this AD, and thereafter at intervals not to exceed 240 landings from the last inspection, in accordance with BAC 1-11 Alert Service Bulletin 32-A-PM 2437, Issue 3, dated February 1, 1967, or later ARB-approved issue. Replace cracked or broken washers and remove washers from service before the accumulation of 8,000 landings. (c) For airplanes with Belleville washers P/N 1383 No. 12 (Terry) installed in the main undercarriage down lock jacks with 7,760 or more landings on the effective date of this AD, remove washers from service within the next 240 landings.(d) For airplanes with Belleville washers P/N AB44-1791 installed in BAC Modification PM 2437 main undercarriage down lock jacks, with less than 15,800 landings on the effective date of this AD, remove washers from service before the accumulation of 16,000 landings. (e) For airplanes with Belleville washers P/N AB44-1791 installed in BAC Modification PM 2437 main undercarriage down lock jacks with 15,800 or more landings on the effective date of this AD, remove washers from service within the next 200 landings. (f) For airplanes with Tonks spring discs, P/N AK43-1283, installed in BAC Modification PM 4676 main landing gear down lock jacks, unless already accomplished, before accumulating 16,000 landings or within the next 3,000 landings after the effective date of this AD, whichever occurs later, remove the spring discs from service in accordance with paragraph 2, "ACCOMPLISHMENT INSTRUCTIONS," of BAC 1-11 Alert Service Bulletin 32-A- PM5700, Issue No. 1, dated May 10, 1979, oran FAA-approved equivalent. (g) For the purpose of complying with this AD, subject to acceptance by the assigned FAA maintenance inspector, the number of landings may be determined by dividing each airplane's hours' time in service by the operator's fleet average time from takeoff to landing for the airplane type. (h) Upon request of an operator, an FAA maintenance inspector, subject to the 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 or at intervals greater than that specified in this AD if the request contains substantiating data to justify the increase for that operator. NOTE - AD 66-24-03 pertains to Belleville washers installed in the nose undercarriage up/down lock jacks. The manufacturer's specifications and procedures identified and described 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 British Aerospace, Inc., Box 17414, Dulles International Airport, Washington, D.C. 20591. These documents may be examined at FAA Headquarters, Room 916, 800 Independence Avenue, SW., Washington, D.C. 20591. Amendment 39-476 became effective September 9, 1967. This amendment 39-4217 becomes effective October 14, 1981.
72-16-04: 72-16-04 SIAI-MARCHETTI: Amendment 39-1488. Applies to Siai Marchetti Models S.205-18/R, S.205-20/R, and S.205-22/R airplanes, Serial Numbers 106 through 239. Compliance required as indicated unless already accomplished. To detect and prevent cracks in the nose gear drag link assembly, accomplish the following: (a) Within the next 10 hours' time in service after the effective date of this AD, unless already accomplished within the last 15 hours' time in service, and thereafter at intervals not to exceed 25 hours' time in service from the last inspection, visually inspect the tubes and welded areas of the nose gear articulated drag brace rear link, P/N 205-9-142-03, using a magnifying glass of 5 power or more. If indications of cracks are found, strip the paint from the area and reinspect using a magnifying glass of 5 power or more. (b) If any cracks or breaks are found during the inspections required by paragraph (a), before further flight, remove the nose gear dragbrace assembly, P/N 205-9-142-01, and accomplish one of the following: (1) Install reinforced nose gear dray brace assembly, P/N 205-9-142-05 or P/N 205-9-142-09, in accordance with SIAI-Marchetti Service Bulletin No. 205B12A, dated January 21, 1972, or an FAA-approved equivalent; or (2) Comply with subparagraph (i) or (ii), as applicable, in accordance with SIAI-Marchetti Service Instruction No. 205SI-16, dated March 29, 1972, or an FAA-approved equivalent. (i) For Model S.205-18/R and -20/R airplanes, install press formed nose gear drag brace assembly, P/N 205-9-142-103. (ii) For Model S.205-22/R airplanes, install press formed nose gear drag brace assembly, P/N 205-9-142-103, and replace the bellcrank, P/N 205-6-062-03, with bellcrank, P/N 205-6-062-107. (c) The repetitive inspections required by paragraph (a) may be discontinued when a reinforced or press formed nose gear drag brace assembly is installed in accordance with paragraph (b)(1) or (b)(2)(i) for Models S.205-18/R and -20/R airplanes, or when a reinforced nose gear drag brace assembly is installed in accordance with paragraph (b)(1) or a press formed nose gear drag brace assembly and a bellcrank, P/N 205-6-062-107, are installed in accordance with paragraph (b)(2)(ii) for the Model S.205-22/R airplanes. This amendment becomes effective July 25, 1972.
2015-12-09 R1: We are revising airworthiness directive (AD) 2015-12-09 for Airbus Helicopters Model EC135P1, EC135T1, EC135P2, EC135T2, EC135P2+, EC135T2+, and MBB-BK 117 C-2 helicopters. AD 2015-12-09 required inspecting certain washers for movement and making the appropriate repairs if the washers move. As published, AD 2015-12-09 referenced an incorrect date for the service information in the Credit for Previous Actions section. This AD corrects the error while retaining the requirements of AD 2015-12-09. These actions are intended to prevent loss of concerned control axis and subsequent loss of control of the helicopter.
2002-23-04: This amendment adopts a new airworthiness directive (AD) for the specified Eurocopter France (ECF) model helicopters that requires inspecting the 9-degree frame (frame) for the correct edge distance of the two attachment holes for the reinforced latch support and for a crack and repairing the frame if necessary. This amendment is prompted by the detection of a fatigue crack on the left-hand (LH) side of the frame during maintenance. The actions specified by this AD are intended to prevent failure of the frame due to a crack at the latch support, loss of a passenger door, damage to the rotor system, and subsequent loss of control of the helicopter.