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92-19-09 R1: 92-19-09 R1 SHORT BROTHERS, PLC: Amendment 39-8716. Docket 93-NM-61-AD. Revises AD 92-19-09, Amendment 39-8367, which superseded AD 84-07-06 R1, Amendment 39-6036. Applicability: All Model SD3-30 series airplanes, certificated in any category. Compliance: Required as indicated, unless accomplished previously. NOTE 1: Paragraphs (a), (b), (c), and (f) of this AD restate the requirements of those paragraphs as they appeared in AD 92-19-09, Amendment 39-8367; the requirements of those paragraphs entail specific one-time actions. As allowed by the phrase, "unless accomplished previously," if the requirements of those paragraphs have been accomplished previously, this AD does not require that they be repeated. NOTE 2: Paragraphs (d) and (e) of this AD restate the requirements for repetitive inspections contained in the same paragraphs of AD 92-19-09, Amendment 39-8367. The first inspection required by this AD must be performed within the specified repetitive inspection interval after the last inspection performed in accordance with paragraphs (d) and (e) of AD 92-19-09. To prevent reduced structural capability of the wing, accomplish the following: (a) Within 180 days after November 3, 1988 (the effective date of AD 84-07-06 R1, Amendment 39-6036), install a new closing panel in the aft baggage compartment in accordance with Shorts Service Bulletin SD3-25-30, dated January 8, 1982. (b) Within 180 days after November 3, 1988, inspect to detect fuel leakage and seal the fuselage crown in accordance with Shorts Service Bulletins SD3-53-01, Revision 2, dated January 19, 1977; SD3-53-18, dated November 25, 1977; and SD3-53-41, dated May 21, 1980. (c) Within 600 hours time-in-service after November 3, 1988, or prior to the accumulation of 4,800 total hours time-in-service, whichever occurs later, inspect to detect cracking and modify the wing drag links in accordance with Shorts Service Bulletin SD3-53-48, Revision 1, dated January 5, 1983. Replace damaged parts prior to further flight, in accordance with the service bulletin. (d) Within 90 days after November 3, 1988, inspect to detect corrosion or wear in the horizontal stabilizer (tailplane)-to-fuselage fittings, pins, and bushings in accordance with Shorts Service Bulletin SD3-55-16, Revision 3, dated November 1987. For airplanes that have accumulated less than 4,800 total hours time-in-service and are less than 2 years old as of November 3, 1988, accomplishment of this inspection may be deferred until the affected airplane reaches 4,800 total hours time-in-service or 2 years of age, whichever occurs first. Replace any worn or corroded parts prior to further flight, in accordance with the service bulletin. (1) If no pin has been replaced with a new pin, and if there is no corrosion found on any attachment fitting, repeat this inspection thereafter at intervals not to exceed 1,200 flight hours or within 6 months following the immediately preceding inspection, whichever occurs first. (2) If all the pins on one side have been replaced with new pins, repeat the inspection on that side within the next 4,800 flight hours or 2 years following replacement of the pins, whichever occurs first. Repeat this inspection thereafter at intervals not to exceed 2,400 flight hours or 1 year following the immediately preceding inspection, whichever occurs first. (e) For airplanes having serial numbers SH3002 through SH3090, inclusive: Within 300 hours time-in-service after November 3, 1988, or prior to the accumulation of 4,800 total hours time- in-service, whichever occurs later, inspect to detect cracked or broken rib/skin attachment cleats at left wing station 160 in accordance with Part A (Inspection) of paragraph 2.A. of the Accomplishment Instructions in Shorts Service Bulletin SD3-57-10, Revision 1, dated October 11, 1982; or Revision 2, dated January 4, 1993. Repeat this inspection within 2,400 hours time-in-service following the immediately preceding inspection, or within 300 hours time-in-service after November 17, 1992 (the effective date of AD 92-19-09, Amendment 39-8367), whichever occurs later. (1) If no crack is found, repeat this inspection of each bay thereafter at intervals not to exceed 2,400 hours time-in-service. (2) If any crack is found, prior to further flight, repair in accordance with Part B (Repair - Rear Bay) and/or Part C (Repair - Forward Bay) of paragraph 2.A. of the Accomplishment Instructions in the service bulletin; and repeat the inspection of the repaired bay thereafter at intervals not to exceed 9,600 hours time-in-service. (f) Within 180 days after November 3, 1988, modify the power control circuit in accordance with Shorts Service Bulletin SD3-76-01, dated September 8, 1981. (g) An alternative method of compliance or adjustment of the compliance time that provides an acceptable level of safety may be used if approved by the Manager, Standardization Branch, ANM-113, FAA, Transport Airplane Directorate. Operators shall submit their requests through an appropriate FAA Principal Maintenance Inspector, who may add comments and then send it to the Manager, Standardization Branch, ANM-113. NOTE 3: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Standardization Branch, ANM-113. (h) 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. (i) The actions shall be done in accordance with Shorts Service Bulletin SD3-25-30, dated January 8, 1982; Shorts Service Bulletin SD3-53-01, Revision 2, dated January 19, 1977; Shorts Service Bulletin SD3-53-18, dated November 25, 1977; Shorts Service Bulletin SD3-53-41, dated May 21, 1980; Shorts Service Bulletin SD3-53-48, Revision 1, dated January 5, 1983; Short Service Bulletin SD3-55-16, Revision 3, dated November 1987; Shorts Service Bulletin SD3-76-01, dated September 8, 1981; Shorts Service Bulletin SD3-57-10, Revision 1, dated October 11, 1982; and Shorts Service Bulletin SD3-57-10, Revision 2, dated January 4, 1993. Revision 2 of Shorts Service Bulletin SD3-57-10 contains the following list of effective pages: Page Number Revision Level Shown on Page Date Shown on Page 1, 3-13 1 October 11, 1982 2 2 January 4, 1993 This incorporation by reference of Shorts Service Bulletin SD3-57-10, Revision 2, dated January 4, 1993, is approved by the Director of the Federal Register in accordance with 5 U.S.C. 552(a) and 1 CFR Part 51. The incorporation by reference of the remainder of the service documents listed above was approved previously by the Director of the Federal Register in accordance with 5 U.S.C. 552(a) and 1 CFR Part 51 as of November 17, 1992 (57 FR 46772, October 13, 1992). Copies may be obtained from Short Brothers, PLC, 2011 Crystal Drive, Suite 713, Arlington, Virginia 22202-3719. Copies may be inspected at the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington; or at the Office of the Federal Register, 800 North Capitol Street, NW., suite 700, Washington, DC. (j) This amendment becomes effective on November 26, 1993.
2017-02-05: We are adopting a new airworthiness directive (AD) for all The Boeing Company Model 737-100, -200, -200C, -300, -400, and -500 series airplanes. This AD was prompted by reports of skin cracking found at the corners of the aft entry and aft galley doorways. This AD requires repetitive inspections for cracking of the fuselage \n\n((Page 9493)) \n\nskin assembly and the bear strap at the corners of the aft entry and aft galley doorways, and repair if necessary, which terminates the repetitive inspections of the repaired areas. We are issuing this AD to address the unsafe condition on these products.
2017-02-06: We are adopting a new airworthiness directive (AD) for certain Piper Aircraft, Inc. Models PA-31T, PA-31T1, PA-31T2, PA-31T3, and PA- 31P-350 airplanes. This AD requires repetitive detailed visual inspections of the wiring below the main circuit breaker panel for proper clearance and evidence of damage and rerouting or replacing wires and/or parts as necessary. This AD was prompted by a fatal accident where evidence of thermal damage in this area was found. We are issuing this AD to correct the unsafe condition on these products.
2001-17-22: This amendment adopts a new airworthiness directive (AD), applicable to certain McDonnell Douglas Model DC-10 and MD-10 series airplanes, that requires an inspection of the one phase remote control circuit breakers (RCCB) in the main avionics compartment and center accessory compartment to determine their part numbers and serial numbers, and replacement of RCCB's with certain RCCB's, if necessary. This action is necessary to ensure that defective braze joints of certain latch assemblies of the RCCB are not installed on the airplane. Defective braze joints could fail and prevent the RCCB from tripping during an overload condition, which could result in a fire and smoke in certain wire bundles that are routed to and from the main avionics compartment or center accessory compartment. This action is intended to address the identified unsafe condition.
92-18-10: 92-18-10 BRITISH AEROSPACE: Amendment 39-8354. Docket 92-NM-34-AD. Applicability: Model ATP series airplanes; serial numbers 2001 through 2045, inclusive; which have been modified in accordance with Pratt and Whitney Service Bulletin PW100-72-21097, dated November 8, 1991; certificated in any category. Compliance: Required as indicated, unless accomplished previously. To prevent severe structural damage to the airplane due to an internal engine fire within the intercompressor case, accomplish the following: (a) Within 90 days after modification in accordance with Pratt and Whitney Service Bulletin PW100-72-21097, dated November 8, 1991, or within 90 days after the effective date of this AD, whichever occurs later: (1) Install an intercompressor case (ICC) fire detector system, in accordance with British Aerospace Service Bulletin ATP-26-5-35225A, dated October 30, 1991. (2) Revise Section 0.25.0 of the FAA-approved Airplane Flight Manual (AFM) to include the following statement. This may be accomplished by inserting a copy of this AD in the AFM. "Modification No. Description 35225A Introduction of ICC Fire Detector at the Intercompressor Case." (3) Revise the FAA-approved AFM to include operating information pertaining to the ICC fire detection systems. This may be accomplished by inserting a copy of Temporary Revision No. T/24, Issue 1, dated February 17, 1992, into the AFM. (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, Standardization Branch, ANM-113, FAA, Transport Airplane Directorate. Operators shall submit their requests through an appropriate FAA Principal Maintenance Inspector, who may add comments and then send it to the Manager, Standardization Branch, ANM-113. NOTE: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Standardization Branch. (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 installation and revision of the AFM shall be done in accordance with Temporary Revision No. T/24, Issue 1, dated February 17, 1992; and British Aerospace Service Bulletin ATP-26-5-35225A, dated October 30, 1991, which contains the following list of effective pages: Page Number Revision Level Date 1-7, 9, 11, 13, 15, 17, 19, 21, 23, 25, 27, 29, 31, 33, 35, 37, 39, 41, 43 Original October 30, 1991 8, 10, 12, 14, 16, 18, 20, 22, 24, 26, 28, 30, 32, 34, 36, 38, 40, 42 (These pages are not used) 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 British Aerospace, PLC, Librarian for Service Bulletins,P.O. Box 17414, Dulles International Airport, Washington, DC 20041-0414. Copies may be inspected at the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington; or at the Office of the Federal Register, 800 North Capitol Street, NW., Suite 700, Washington, DC. (e) This amendment becomes effective on October 13, 1992.
2017-01-03: We are superseding Airworthiness Directive (AD) 2007-11-13 for all The Boeing Company Model 717-200 airplanes. AD 2007-11-13 required revising the Airworthiness Limitations Section (ALS) of the Instructions for Continued Airworthiness to incorporate new removal limits for certain components of the flap system and to reduce the inspection intervals for fatigue cracking of principal structural elements (PSE). This new AD requires revising the maintenance or inspection program, as applicable, to incorporate reduced intervals for the inspections for three PSEs and add nondestructive inspections (NDIs). This AD was prompted by a new Airworthiness Limitations Instruction (ALI) revision that incorporates NDI techniques and reduced repetitive inspection intervals for three PSEs. We are issuing this AD to address the unsafe condition on these products. \n\n((Page 9496))
2001-17-19: This amendment adopts a new airworthiness directive (AD), applicable to all McDonnell Douglas Model DC-10 series airplanes, and KC-10A and KDC-10 (military) airplanes, that requires certain modifications of the thrust reverser control and indication system and wiring on each engine. This amendment is prompted by a determination that the current thrust reverser systems do not adequately preclude unwanted deployment of a thrust reverser. These actions are necessary to prevent unwanted deployment of a thrust reverser, which could significantly jeopardize continued safety of flight and landing of the airplane.
2017-01-01: We are superseding airworthiness directive (AD) 2014-05-25 for all Rolls-Royce plc (RR) RB211-Trent 970-84, RB211-Trent 970B-84, RB211-Trent 972-84, RB211-Trent 972B-84, RB211-Trent 977-84, RB211- Trent 977B-84, and RB211-Trent 980-84 turbofan engines. AD 2014-05-25 required inspections of the low-pressure turbine (LPT) exhaust case and support assembly or tail bearing housing (TBH) to detect cracks or damage. This AD modifies the inspection schedule for the affected engines and adds an optional terminating action. This AD was prompted by RR performing additional analysis of inspection results and determining that the existing inspections need to be modified. We are issuing this AD to correct the unsafe condition on these products.
2010-24-02: We are adopting a new airworthiness directive (AD) for the products listed above. This AD results from mandatory continuing airworthiness information (MCAI) originated 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: A design review has shown that the Lightning Sensor System (LSS) antenna which is optionally installed on certain Falcon 7X aeroplanes might, in the event of belly or gear-up landing, puncture the rear fuel tank, which could result in fuel leakage and post- landing fire. We are issuing this AD to require actions to correct the unsafe condition on these products.
2001-17-14: This amendment adopts a new airworthiness directive (AD) that is applicable to CFM International (CFMI) CFM56-5C4/1 series turbofan engines. This action requires that the LPT conical support, P/N 337-002-407-0, installed in CFM56-5C4/1 engines, be removed from service at or before reaching the cyclic life limit of 9,350 cycles-since-new (CSN). This amendment is prompted by the discovery of an error in the Time Limits Section of Chapter 5 of the CFM56-5C Engine Shop Manual. The manual incorrectly lists the published cyclic life limit of the CFMI CFM56-5C4/1 LPT conical support, (P/N) 337-002-407-0, as 15,000 CSN, rather than the certified value of 9,350 CSN. The actions specified in this AD are intended to prevent LPT conical supports from remaining in service beyond their certified cyclic life limit, which could result in an uncontained engine failure and damage to the airplane.