Results
2015-17-14: We are adopting a new airworthiness directive (AD) for all Airbus Model A319, A320, and A321 series airplanes. This AD was prompted by reports that during a full scale fatigue test, several broken frames in certain areas of the cargo compartment have been found, especially on the cargo floor support fittings and open tack holes on the left-hand side. This AD requires a rototest inspection of the open tack holes and rivet holes at the cargo floor support fittings of the fuselage, including doing all applicable related investigative actions, and repair if necessary. We are issuing this AD to detect and correct cracking in the open tack holes and rivet holes at the cargo floor support fittings of the fuselage, which could affect the structural integrity of the airplane.
89-03-01 R1: 89-03-01 R1 GOODYEAR: Amendment 39-6103 as revised by Amendment 39-6334. Applicability: 32x8.8R16, 10PR, P/N 328Q08G2 radial tires, with serial dates 8060Gxxx and above, installed on but not limited to ATR-42 aircraft. Compliance: Required as indicated, unless already accomplished. To prevent tire failure, accomplish the following: (a) Remove from service, all tires with serial dates between 8060Gxxx and 8320Gxxx, as follows: (1) Tires which have accumulated 250 or more landings since new on the effective date of this AD, within the next 50 landings. (2) Tires which have accumulated less than 250 landings since new on the effective date of this AD, at or prior to accumulating 300 landings. (3) Tires for which no landing record has been maintained, within the next 50 landings. (b) Remove from service, all tires with serial dates 8340Gxxx and above, as follows: (1) Tires which have accumulated 250 or more landings since new on the effective date of this AD, within the next 150 landings. (2) Tires which have accumulated less than 250 landings since new on the effective date of this AD, at or prior to accumulating 400 landings. (3) Tires for which no landing record has been maintained, within the next 150 landings. NOTES: (1) Tires with serial dates 8060Gxxx and above may be used as replacements subject to the restrictions of paragraphs (a) and (b) above. Tires with serial dates prior to 8060Gxxx are approved without restrictions. (2) Goodyear Alert Service Bulletins 32-001, dated December 5, 1988, and 32-002, Revision 1, dated July 14, 1989, apply to this AD. (c) 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. (d) Upon submission of substantiating data by an owner or operator through an FAA Airworthiness Inspector, an alternate method of compliance with the requirements of this AD or adjustments to the compliance times specified in this AD may be approved by the Manager, Boston Aircraft Certification Office, Engine and Propeller Directorate, Aircraft Certification Service, Federal Aviation Administration, 12 New England Executive Park, Burlington, Massachusetts 01803. This AD revises AD 89-03-01, Amendment 39-6103 (54 FR 1342; January 13, 1989) which became effective on February 12, 1989. This amendment (39-6334, AD 89-03-01 R1) becomes effective on November 13, 1989.
2002-05-03: This amendment supersedes an existing airworthiness directive (AD), that is applicable to General Electric Company (GE) CF6-6, CF6- 45, and CF6-50 series turbofan engines, that currently requires revisions to the Time Limits Section of the manufacturer's Instructions for Continued Airworthiness (ICA) to include required inspection of selected critical life-limited parts at each piece-part exposure. This amendment modifies the airworthiness limitations section of the manufacturer's manual and an air carrier's approved continuous airworthiness maintenance program to incorporate additional inspection requirements. A Federal Aviation Administration (FAA) study of in- service events involving uncontained failures of critical rotating engine parts has indicated the need for mandatory inspections. The mandatory inspections are needed to identify those critical rotating parts with conditions, which if allowed to continue in service, could result in uncontained failures. The actions specified by this AD are intended to prevent critical life-limited rotating engine part failure, which could result in an uncontained engine failure and damage to the airplane.
2022-22-10: The FAA is superseding Airworthiness Directive (AD) 2020-21- 11, which applied to certain Airbus SAS Model A318 series airplanes; Model A319-111, -112, -113, -114, -115, -131, -132, -133, -151N, and - 153N airplanes; and Model A320 and A321 series airplanes. AD 2020-21-11 required revising the existing maintenance or inspection program, as applicable, to incorporate new or more restrictive airworthiness limitations. This AD was prompted by a determination that new or more restrictive airworthiness limitations are necessary. This AD continues to require the actions in AD 2020-21-11 and requires revising the existing maintenance or inspection program, as applicable, to incorporate additional new or more restrictive airworthiness limitations, 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.
90-13-04: 90-13-04 SAAB-SCANIA: Amendment 39-6631. Docket No. 90-NM-16-AD. Applicability: Model SF-340A series airplanes, Serial Numbers 004 through 108, inclusive, certificated in any category. Compliance: Required prior to the accumulation of 16,000 landings or within 30 days after the effective date of this AD, whichever occurs later, unless previously accomplished. To prevent fatigue damage and reduced structural integrity of the wings, accomplish the following: A. Remove the four fasteners in the lower part of the wing/fuselage attachment fitting at Wing Station 42.3 (left and right wings), enlarge the holes, and inspect for cracks using a non-destructive testing method (eddy current), in accordance with SAAB-Scania Service Bulletin 340-57-017, dated December 1, 1989. 1. If no cracks are found, prior to further flight, install oversize fasteners in accordance with the service bulletin. 2. If cracks are found, prior to further flight, further enlarge theholes and install oversize fasteners, in accordance with the service bulletin. The holes may be enlarged up to 0.264/0.262 inch (6,706/6,655 mm). 3. If cracks are still found following the maximum reaming allowed, repair prior to further flight, in a manner approved by the Manager, Standardization Branch, ANM-113, FAA, Northwest Mountain Region. B. An alternate means of compliance or adjustment of the compliance time, which provides an acceptable level of safety, may be used when approved by the Manager, Standardization Branch, ANM- 113, FAA, Northwest Mountain Region. NOTE: The request should be forwarded through an FAA Principal Maintenance Inspector (PMI), who will either concur or comment and then send it to the Manager, Standardization Branch, ANM-113. C. Special 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. All persons affected by this directivewho have not already received the appropriate service documents from the manufacturer may obtain copies upon request to SAAB-Scania, Product Support, S- 581.88, Linkoping, Sweden. These documents may be examined at the FAA, Northwest Mountain Region, Transport Airplane Directorate, 17900 Pacific Highway South, Seattle, Washington, or the Standardization Branch, 9010 East Marginal Way South, Seattle, Washington. This amendment (39-6631, AD 90-13-04) becomes effective on July 23, 1990.
2002-04-08: This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 737-600, -700, -700C, and -800 series airplanes, that requires a one-time inspection of certain fasteners in rudder pedal housings to determine if pan-head fasteners are installed, and replacement of existing fasteners with improved fasteners, if necessary. The actions specified by this AD are intended to prevent loss of free movement of the rudder pedals, which could result in reduced controllability of the airplane. This action is intended to address the identified unsafe condition.
89-07-17: 89-07-17 MCDONNELL DOUGLAS: Amendment 39-6169. \n\n\tApplicability: Model DC-9 series, Model DC-9-80 series, Model MD-88, and C-9 (military) series airplanes, certificated in any category. \n\n\tCompliance: Required as indicated, unless previously accomplished. \n\n\tTo detect center tank fuel pump failures, accomplish the following: \n\n\tA.\tWithin 10 calendar days after the effective date of this AD, revise the Limitations Section of the FAA-approved Airplane Flight Manual (AFM) to add the following, and provide to flight crews. This may be accomplished by inserting a copy of this AD in the AFM: \n\n\t\tSECTION I - LIMITATIONS \n\n\t\tFUEL MANAGEMENT \n\n\t\tAdd the following wording at the beginning of this section: "Prior to engine start on any flight where center tank fuel is present and will be needed for that route segment, the center tank fuel pumps must be individually checked to verify pump operation. This must be accomplished by observing that both inlet fuel pressure low lights extinguish when each individual center tank pump is activated. \n\n\t\tNOTE: Center tank pumps on aircraft with a center tank fuel pump low pressure warning system installed are not required to be checked in accordance with these procedures." \n\n\tB.\tAn alternate means of compliance or adjustment of the compliance 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. \n\n\t\tNOTE: The request should be forwarded through an FAA Principal Operations Inspector (POI), who may add any comments and then send it to the Manager, Los Angeles Aircraft Certification Office. \n\n\tThis amendment (39-6169, AD 89-07-17) becomes effective on May 4, 1989.
2002-05-01: This amendment supersedes an existing airworthiness directive (AD), applicable to certain Boeing Model 747-100, 747-200, 747-300, 747SP, and 747SR series airplanes powered by Pratt & Whitney JT9D-3 or JT9D-7 series engines. That AD currently requires inspections of the vertical chords of the aft torque bulkhead of the outboard nacelle struts, corrective action, if necessary, and a modification of the vertical chords, which ends the inspections. This amendment will reduce the compliance time and repetitive intervals for the currently required inspections. These actions are necessary to prevent cracking of the vertical chords adjacent to the lower spar fitting, which could result in separation of the diagonal brace load path. Continued operation with a separated diagonal brace load path increases loads on the upper link, midspar fitting, and dual side links, which could result in separation of the strut and engine from the airplane. These actions are intended to address the identified unsafe condition.
2020-03-20: The FAA is adopting a new airworthiness directive (AD) for certain The Boeing Company Model MD-11, MD-11F, and 717-200 airplanes, all Model 737-8 and 737-9 airplanes, all Model 737-600, -700, -700C, - 800, -900, and -900ER series airplanes, certain Model 747-400 and 747- 400F series airplanes, certain Model 757 and 767 airplanes, and all Model 777 airplanes. This AD requires revising the existing airplane flight manual (AFM) to include a limitation to prohibit operations that require less than 0.3 required navigational performance (RNP) within a specified area for airplanes having a certain multi-mode receiver (MMR) with certain software installed. This AD was prompted by reports of the loss of global positioning system (GPS) data or degraded GPS positional accuracy while using a certain MMR. The FAA is issuing this AD to address the unsafe condition on these products.
2015-17-17: We are adopting a new airworthiness directive (AD) for all Pratt & Whitney (PW) PW4164-1D, PW4168-1D, PW4168A-1D and PW4170 engines, and certain PW4164, PW4168, and PW4168A turbofan engines. This AD was prompted by fuel nozzle-to-fuel supply manifold interface fuel leaks. This AD requires inspecting fuel nozzles for signs of leakage, replacing hardware as required, and torqueing to specified requirement. We are issuing this AD to prevent fuel leaks which could result in engine fire and damage to the airplane.