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80-12-10 R1: 80-12-10 R1 BRITISH AEROSPACE (Formerly Hawker Siddeley Aviation, Ltd.): Amendment 39- 3797 as amended by Amendment 39-4524. Applies to Model DH/BH/HS 125 series airplanes except 700 series airplanes above Serial Number NA-0245, certificated in all categories. Compliance is required as indicated. To prevent the possible loss of flaps, accomplish the following: (a) For those airplanes to which AD 78-03-03 did not apply, before further flight, except that the airplane may be flown in accordance with FAR 21.197 and FAR 21.199 to a base where the work can be accomplished, and for those airplanes to which AD 78-03-03 applies, within the next 3 months after the last inspection performed in accordance with AD 78-03-03, unless already accomplished- (1) Incorporate British Aerospace Modification No. 252670 or an FAA-approved equivalent in accordance with all items set forth in paragraph 2, "Accomplishment Instructions," British Aerospace Service Bulletin SB. 57-54-(2670), dated March 10, 1978, or an FAA-approved equivalent; and (2) Concurrently with incorporation of the modification, inspect the aft lug of the hinge arm brackets and, except for 700 series airplanes, trim, blend, and de-burr the reinforcing on the flap lower skin, in accordance with "Additional Action to be Carried Out Concurrently with SB. 57-54 paras. 2.A(4) to (7)," page 8, British Aerospace Service Bulletin SB. 57-54-(2670), dated March 10, 1978, or an FAA-approved equivalent. However, if before the effective date of this AD, an airplane had incorporated Modification 252670 or an FAA-approved equivalent, but any of the actions specified in paragraph (a)(2) of this AD, if applicable, had not been accomplished, comply with paragraph (c) of this AD. (b) For those airplanes which before the effective date of this AD had not incorporated British Aerospace Modification 252670 or an FAA-approved equivalent and had not performed the lug inspection and the trimming, etc., of the reinforcing specified in paragraph (a)(2) of this AD, within the next 12 months after concurrently accomplishing this work in accordance with paragraph (a) of this AD, inspect in accordance with paragraph (e) of this AD. (c) For those airplanes which before the effective date of this AD had already incorporated British Aerospace Modification 252670 or an FAA-approved equivalent (1) Except for 700 series airplanes - (i) Within the next 3 months after the effective date of this AD, unless already accomplished, trim, blend, and de-burr the reinforcing on the flap lower skin in accordance with paragraph 1, "Additional Action to be Carried Out Concurrently With SB. 57-54 para. 2A(4) to (7)," page 8, British Aerospace Service Bulletins 57-54-(2670), dated March 10, 1978, or an FAA-approved equivalent; and (ii) Within the next 3 months after the effective date of this AD but not before paragraph (c)(1) of this AD has been accomplished, inspect in accordance with paragraph (e) of this AD. However, for an airplane on which before the effective date of this AD, British Aerospace Service Bulletin SB. 57-55 dated May 5, 1978, (hereinafter Service Bulletin SB. 57-55) had been accomplished and either before such accomplishment or concurrently with such accomplishment the trimming, etc., of the reinforcing on the flap lower skin specified in paragraph (c)(1) of this AD had been accomplished, within the next 3 months after the effective date of this AD or within the next 12 months after the last accomplishment of Service Bulletin SB. 57-55, whichever occurs later, inspect in accordance with paragraph (e) of this AD. (2) For 700 series airplanes, within the next 3 months after the effective date of this AD or within the next 12 months after the last accomplishment of Service Bulletin SB. 57-55 of this AD, whichever occurs later, inspect in accordance with paragraph (e) of this AD. (d) Within the next 12 months after the inspection requiredby paragraph (b) or (c) of this AD, and thereafter at intervals not to exceed 12 months from the last inspection, inspect in accordance with paragraph (e) of this AD. (e) Inspect the flap outer hinge assemblies using the dye penetrant method in accordance with paragraph 2, "Accomplishment Instructions" of Service Bulletin SB. 57-55 or an FAA-approved equivalent. This inspection requires full compliance with Items 1 through 7 of paragraph 2 of the Service Bulletin. (f) If, during any inspection required by this AD, any cracks are found: (1) Before further flight - (i) Replace the cracked part with a new part in accordance with Service Bulletin SB. 57-55, or an FAA-approved equivalent. In addition, if the rear lug of a hinge arm is found to be cracked, also replace the associated steel strap with a new strap in accordance with Service Bulletin S.B. 57-55 or an FAA-approved equivalent; (ii) Re-protect and reassemble the assemblies, complying fully with Items 9 through 13, paragraph 2, "Accomplishment Instructions" of Service Bulletin SB. 57-55 or an FAA- approved equivalent. (2) Continue the repetitive inspection required by this AD. (g) If, during any inspection required by this AD, no cracks are found, re-protect and reassemble the assemblies complying fully with Items 9 through 13, paragraph 2, "Accomplishment Instructions" of Service Bulletin SB. 57-55 or an FAA-approved equivalent, and continue the repetitive inspections required by this AD. (h) For purposes of this AD, an FAA-approved equivalent must be approved by the Manager, Aircraft Certification Staff, AEU-100, Europe, Africa, and Middle East Office, FAA, c/o American Embassy, Brussels, Belgium. (i) Accomplishment of BAe Modification 252659 constitutes terminating action for this AD. 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).AD 78-03-03, Amendment 39-3133 was superseded by AD 80-12-10, Amendment 39-3797. Amendment 39-3797 became effective June 23, 1980. This Amendment 39-4524 becomes effective January 3, 1983.
2000-13-04: This amendment supersedes an existing airworthiness directive (AD), applicable to all Boeing Model 777-200 and -300 series airplanes, that currently requires revising the Limitations Section of the Airplane Flight Manual (AFM) to prohibit the dispatch of certain airplanes under certain conditions. That amendment also requires repetitive inspections to ensure correct operation of the backup generators; and, for certain airplanes, a one-time inspection to detect damage of the engine external gearbox; and corrective actions, if necessary. This amendment continues the AFM and inspection requirements and expands certain corrective action requirements. This amendment is prompted by reports of inflight shutdowns due to sheared backup generator shafts. The actions specified in this AD are intended to prohibit the dispatch of an airplane with an engine-mounted backup generator having a sheared shaft; and to detect and correct damage to the engine, which could result in inflightshutdowns.
2000-13-02: This amendment adopts a new airworthiness directive (AD) that is applicable to certain EMBRAER Model EMB-135 and EMB-145 series airplanes. This action requires revising the Airplane Flight Manual, and eventual disconnection of the precooler differential pressure switches. This action is necessary to prevent incorrect operation of the precooler differential pressure switches, which could result in inappropriate automatic shutoff of the engine bleed valve, and consequent inability to restart a failed engine using cross-bleed from the other engine or possible failure of the anti-ice system. This action is also necessary to ensure that the flight crew is advised of the procedures necessary to restart an engine in flight using the auxiliary power unit.
70-20-01: 70-20-01 SIAI-MARCHETTI: Amdt. 39-1081. Applies to Model 205-22/R airplanes. To prevent malfunction of the flap position locking mechanism, within the next 25 hours' time in service after the effective date of this AD, unless already accomplished, replace the flap system locking pawl (P/N 205-6-052-22) and cup (P/N 205-6-052-23) with a modified locking pawl (P/N 205-6-052-22/A) and modified cup (P/N 205-6-052-23/A) in accordance with SIAI Marchetti Technical Instruction No. 205 I-13, dated 3 April 1970, or an FAA-approved equivalent. (SIAI Marchetti Service Bulletin No. 205B25 refers to this subject). This amendment becomes effective September 22, 1970.
2022-20-02: The FAA is adopting a new airworthiness directive (AD) for all Airbus SAS Model A350-1041 airplanes. This AD was prompted by a potential interference between the ram air turbine (RAT) blade tip and the belly fairing (BF) RAT inboard door. This AD requires replacing the BF inboard RAT door and BF adjacent panels, and prohibits the installation of affected parts, as specified in a European Union Aviation Safety Agency (EASA), which is incorporated by reference. The FAA is issuing this AD to address the unsafe condition on these products.
2015-16-08: We are superseding Airworthiness Directive (AD) 2011-08-51 for certain The Boeing Company Model 737-300, -400, and -500 series airplanes. AD 2011-08-51 required repetitive inspections of the lap joint at certain stringers along the entire length from certain body stations. This new AD expands the inspection area, requires additional inspections for cracks and open pockets, requires corrective actions if necessary, and revises the compliance times. This AD was prompted by an evaluation by the design approval holder (DAH) that has determined that the lower fastener holes in the lower skin of the fuselage lap splice are subject to widespread fatigue damage (WFD). We are issuing this AD to detect and correct fatigue cracking of the lower fastener holes in the lower skin of the fuselage lap splice, which could result in reduced structural integrity of the airplane.
2000-13-03: This amendment adopts a new airworthiness directive (AD), applicable to certain McDonnell Douglas Model DC-8 series airplanes that have been converted from a passenger to a cargo-carrying ("freighter") configuration, that requires a revision to the Airplane Flight Manual Supplement to ensure that the main deck cargo door is closed, latched, and locked; inspection of the door wire bundle to detect discrepancies and repair or replacement of discrepant parts. This amendment also requires, among other actions, modification of the hydraulic and indication systems of the main deck cargo door, and installation of a means to prevent pressurization to an unsafe level if the main deck cargo door is not closed, latched, and locked. This amendment is prompted by the FAA's determination that certain main deck cargo door systems do not provide an adequate level of safety, and that there is no means to prevent pressurization to an unsafe level if the main deck cargo door is not closed, latched, and locked. The actions specified by this AD are intended to prevent opening of the cargo door while the airplane is in flight, and consequent rapid decompression of the airplane including possible loss of flight control or severe structural damage.
2000-12-18: This amendment adopts a new airworthiness directive (AD), applicable to Rolls-Royce Ltd. Dart 511, 511-7E, 514-7, 528, 528-7E, 529-7E, 532-7, 532-7L, 532-7N, 532-7P, 532-7R, 535-7R, 551-7R, and 552-7R turboprop engines. This AD requires the installation of a feathering probe and a steel retaining ring in the reduction gear housing (RGH) and replacement of a transfer bobbin installed in the torquemeter. This amendment is prompted by two reports of the failure of a propeller to feather following the failure of the RGH annulus gear, which resulted in the propeller overspeeding and the release of a propeller blade, causing damage to the airplane. The actions specified by this AD are intended to prevent a propeller from overspeeding and the release of a propeller blade after a failure of the RGH annulus gear, which could result in damage to an adjacent engine or to the airplane.
88-07-51 R1: 88-07-51 R1 LOCKHEED AERONATUICAL SYSTEMS COMPANY: Amendment 39- 5923 as revised by Amendment 39-6311. (Docket No. 88-NM-210-AD) Applicability: Model L-1011-385-1, L-1011-385-1-14, L-1011-385-1-15, and L-1011- 385-3 series airplanes, as listed in Lockheed TriStar L-1011 Service Bulletin 093-29-A088, dated April 14, 1988, certificated in any category. Compliance: Required as indicated, unless previously accomplished. To prevent a fire from a failed AC electrical motor-driven hydraulic pump electrical connector, in combination with leaking hydraulic fluid from the failed electro-hydraulic component, accomplish the following: A. Within 100 flight hours after June 3, 1988 (which is the effective date of Amendment 39-5923), accomplish the following: 1. On the Flight Engineer/Second Officer's (FE/SO) overhead CB panel CB2, open and collar circuit breakers L12 "AC Pump B3" and L22 "AC Pump C3", using PACO plastic ring P/N S-4933959-503 or equivalent. 2.As a verification that power has been removed from affected pumps, on the FE/SO hydraulic system control panel, cycle the AC pumps switch lights and verify that the "ON" legends do not illuminate. B. Accomplishment of the requirements of paragraph A., above, in accordance with Lockheed TriStar L-1011 Alert Service Bulletin 093-29-A088, dated April 14, 1988, is considered an acceptable means of compliance with this AD. C. Installation of an AC Hydraulic Pump Magnetic Circuit Breaker Panel (MCBP) in the Mid-Electrical Service Center (MESC) and associated aircraft wiring, in accordance with Lockheed TriStar L-1011 Service Bulletin 093-29-088, Revision 1, dated March 7, 1989, constitutes terminating action for the requirements of paragraph A., above. The hydraulic pumps may then be reactivated by removing the circuit breaker collars installed in accordance with paragraph A.1., above, and closing the circuit breakers. D. An alternate means of compliance or adjustment of thecompliance time, which provides an acceptable level of safety, may be used when approved by the Manager, Los Angeles Aircraft Certification Office, FAA, Northwest Mountain Region. NOTE: This request should be forwarded through an FAA Principal Maintenance Inspector (PMI), who will either concur or comment and then send it to the Manager, Los Angeles Aircraft Certification Office, FAA, Northwest Mountain Region. All persons affected by this directive who have not already received the appropriate service documents from the manufacturer may obtain copies upon request to Lockheed Aeronautical Systems Company, P.O. Box 551, Burbank, California 91520, Attention: Commercial Order Administration, Department 65-33, Unit 20, Plant A-1. These documents may be examined at the FAA, Northwest Mountain Region, Transport Airplane Directorate, 17900 Pacific Highway South, Seattle, Washington, or the Los Angeles Aircraft Certification Office, 3229 East Spring Street, Long Beach, California.This amendment (39-6311) amends Amendment 39-5923, AD 88-07-51 which became effective on June 3, 1988. This amendment (39-6311, AD 88-07-51 R1) becomes effective on October 2, 1989.
2000-12-20: This amendment adopts a new airworthiness directive (AD), applicable to certain Airbus Model A310 series airplanes, that requires modification of the position 1 flap screw jack. This amendment is prompted by issuance of mandatory continuing airworthiness information by a foreign civil airworthiness authority. The actions specified by this AD are intended to prevent fracture of the lead screw of the position 1 flap screw jack, which could result in failure of the tie bar and possible disconnection of the flap structure from the airplane.