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91-03-03: 91-03-03 PRATT & WHITNEY: Amendment 39-6838. Docket No. 88-ANE-37.
Applicability: Pratt & Whitney (PW) JT9D-7R4 series turbofan engines, installed on, but not limited to, Boeing 747 and 767, and Airbus A310 and A300 aircraft.
Compliance: Required as indicated, unless previously accomplished.
To prevent failure of high pressure compressor (HPC) turbine driveshaft, Part Numbers (P/N) 5001195-01, 796245, 799570, and 803128, which could result in loss of engine power, and/or engine inflight shutdown, accomplish the following:
(a) Eddy current inspect rear threads of the HPC turbine driveshaft, in accordance with PW Alert Service Bulletin (SB) JT9D-7R4-72-375, Revision 2, dated December 22, 1989, and remove from service and replace HPC turbine driveshafts found cracked with a serviceable part as follows:
(1) For those HPC turbine driveshafts which have not been inspected prior to the effective date of this AD, in accordance with PW SB JT9D-7R4-72-365, dated June 23, 1988; PW SB JT9D-7R4-72-365, Revision 1, dated July 12, 1988; PW Alert SB JT9D-7R4-72-375, dated October 28, 1988; or PW Alert SB JT9D- 7R4-72-375, Revision 1, dated January 25, 1989, inspect in accordance with the following schedule:
(i) At the next shop visit or prior to accumulating 7,500 cycles in service (CIS), whichever occurs first, those HPC turbine driveshafts with 7,000 CIS or less on the effective date of this AD.
(ii) At the next shop visit or prior to accumulating 500 CIS, whichever occurs first, those HPC turbine driveshafts with greater than 7,000 CIS on the effective date of this AD.
(2) For those HPC turbine driveshafts which have been previously inspected prior to the effective date of this AD, in accordance with PW SB JT9D-7R4-72-365, dated June 23, 1988; PW SB JT9D-7R4-72-365, Revision 1, dated July 12, 1988; PW Alert SB JT9D-7R4-72-375, dated October 28, 1988; or PW Alert SB JT9D- 7R4-72-375, Revision 1, dated January 25, 1989, inspect in accordance with the following schedule:
(i) At the next shop visit or prior to accumulating 7,500 CIS, whichever occurs first; or not to exceed 2,500 cycles since last inspection (CSLI), whichever occurs later, those HPC turbine driveshafts with 7,000 CIS or less on the effective date of this AD.
(ii) At the next shop visit or prior to accumulating 500 CIS whichever occurs first; or not to exceed 2,500 CSLI, whichever occurs later, those HPC turbine driveshafts with greater than 7,000 CIS on the effective date of this AD.
(3) Shop visit definition for the purpose of this AD is anytime the low pressure turbine module is removed.
(b) Eddy current reinspect HPC turbine driveshafts, in accordance with PW Alert SB JT9D-7R4-72- 375, Revision 2, dated December 22, 1989, at intervals not to exceed 2,500 CSLI. Remove from service and replace HPC turbine driveshafts found cracked with a serviceable part.
(c) Reduce the low cycle fatigue (LCF) limit of the HPC turbine driveshaft P/N 5001195-01, 796245, and 799570, from 30,000 cycles to 2,000 cycles, and P/N 803128 from 30,000 cycles to 3,200 cycles, in accordance with the following schedule:
(1) After the effective date of this AD for new HPC turbine driveshafts, with no previous cycles in service, installed in PW JT9D-7R4 series engines.
(2) Prior to January 1, 1995, for those HPC turbine driveshafts installed in any PW JT9D-7R4 series engines, except for the PW JT9D-7R4G2 model engines.
(3) Prior to January 1, 1999, for those HPC turbine driveshafts installed in PW JT9D-7R4G2 model engines.
(d) Remove from service HPC turbine driveshafts installed in PW JT9D-7R4 series engines prior to exceeding the reduced LCF life limit.
(e) Inspections in accordance with paragraphs (a) and (b) of this AD are no longer required for HPC turbine driveshafts with reduced LCF limits.
(f) 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.(g) 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, Engine Certification Office, Engine and Propeller Directorate, Aircraft Certification Service, FAA, 12 New England Executive Park, Burlington, Massachusetts 01803.
The inspection and removal procedures shall be done in accordance with the following Pratt & Whitney document:
Document
Page Number
Revision
Date
PW ASB JT9D-7R4-72-375
1, 4
2
12/22/89
PW ASB JT9D-7R4-72-375
2, 3, 6, 8 thru 15
Original
10/28/88
PW ASB JT9D-7R4-72-375
5, 7
1
01/25/89
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 Pratt & Whitney, Publications Department, P.O. Box 611, Middletown, Connecticut06457. Copies may be inspected at the Regional Rules Docket, Office of the Assistant Chief Counsel, FAA, New England Region, 12 New England Executive Park, Room 311, Burlington, Massachusetts 01803-5299, or at the Office of the Federal Register, 1100 L Street, NW, Room 8301, Washington, DC 20591.
This amendment (39-6838, AD 91-03-03) becomes effective on February 22, 1991.
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92-07-08: 92-07-08 BELL HELICOPTER TEXTRON, INC. (BHTI): Amendment 39-8204. Docket No. 92-ASW-02.
Applicability: Model 204B, 205A, 205A-1, 205B and 212 helicopters, certificated in any category, equipped with swashplate support assembly, part number (P/N) 204-011-404-125.
Compliance: Required as indicated, unless already accomplished.
To prevent possible failure of the swashplate support assembly that could result in loss of the helicopter, accomplish the following:
(a) Within the next 25 hours' time in service after the effective date of this AD, determine the purchase date of the swashplate support assembly, P/N 204-011-404-125, by reviewing the maintenance records. If the assembly was purchased prior to June 1990, no further action is required. If the swashplate support assembly was purchased after June 1990, accomplish the requirements of paragraph (b).
(b) Perform the following:
(1) Disassemble the swashplate support assembly in accordance with the applicable component overhaul manual to the point necessary to allow an inspection of the outboard gimbal ring support lug and shoulder bushing.
(2) Measure the outside diameters (OD) of the bushing flange on each outboard bushing.
(i) If each outboard bushing has a flange OD of 0.61 to 0.64 inches, no further inspections are required.
(ii) If either bushing has a flange OD in excess of 0.64 inches, replace the swashplate support assembly with an airworthy part before further flight.
NOTE: Unapproved bushings with OD's of approximately 0.81 inches have been reported.
(c) Prior to the installation of any swashplate support assembly, P/N 204-011-404-125, comply with this AD.
(d) Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate the helicopter to a location where the requirements of this AD can be accomplished.
(e) An alternative method of compliance or adjustment of the compliance times, which provides an acceptable level of safety, may be used when approved by the Manager, Rotorcraft Certification Office, ASW-170, Rotorcraft Directorate, Aircraft Certification Service, FAA, Southwest Region, 4400 Blue Mound Road, Fort Worth, Texas, 76193-0170. The request shall be forwarded through an FAA Airworthiness Inspector, who may concur or comment and then send it to the Manager of the Rotorcraft Certification Office.
(f) Bell Helicopter Textron, Inc., Alert Service Bulletins 204-91-32, 205-91-45, 205B-91-10, and 212-91-72, all dated December 13, 1991, provide an acceptable, alternate means of compliance with this AD.
(g) This amendment becomes effective on March 25, 1992.
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2015-13-09: We are adopting a new airworthiness directive (AD) for certain Piper Aircraft, Inc. Models PA-46-350P and PA-46-500TP airplanes. This AD requires installing cable ties around the cabin altitude encoder and the supporting structure, adding thread-locking compound to the threads of the existing single fastener; and repetitively inspecting the cable ties and the fastener to ensure security and proper condition. This AD was prompted by a report that a cabin altitude encoder came free from its mounting bracket, which interfered with motion of the elevator flight control. We are issuing this AD to correct the unsafe condition on these products.
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65-16-01: 65-16-01 LOCKHEED: Amdt. 39-101 Part 39 Federal Register June 30, 1965. Applies to Models 188A and 188C Series Aircraft.
Compliance required as indicated.
As a result of cracks, substandard heat treat, and failure of the nose landing gear actuator support link, LAC P/N 750645-3 manufactured by Acor, Inc., under Acor P/N N07011, accomplish the following:
(a) Unless already accomplished within the last 1,700 landings prior to the effective date of this AD, within the next 300 landings after the effective date of this AD, comply with all requirements of (b) (except, that if a hardness check in accordance with (b) was accomplished at any time prior to the effective date of the AD, it need not be reaccomplished), and thereafter at intervals not to exceed 2,000 landings, comply with those requirements of (b) that pertain to crack inspection and replacement of cracked links.
(b) Inspect all Acor, Inc., links for cracks in the necked down area of the link using magnetic particle technique or an FAA-approved equivalent and check the hardness of the Acor, Inc., link flats midway between the bearings. Replace any cracked links and any link on which the heat treat is less than 140,000 p.s.i. before further flight with a new LAC P/N 750645-3 link. If an Acor link is to be installed, its hardness must be checked prior to installation, and its heat treat must be 140,000 p.s.i. or greater. Accomplish this replacement in accordance with sections 2.B(6) through 2.B(10) of Lockheed Service Bulletin 88/SB-612.
(c) The inspections of (b) may be discontinued when LAC P/N 750645-3 link manufactured by Acor, Inc., under Acor P/N N07011 is replaced by a new LAC P/N 750645-3 link manufactured by other than Acor, Inc.
NOTE: LAC P/N 750645-3 link manufactured by Acor, Inc., under Acor P/N N07011 may be identified by its center body thickness which is greater than 0.400 inch.
(d) For the purpose of complying with this AD, subject to acceptance by the assigned FAAmaintenance inspector, the number of landings may be determined by dividing each aircraft's hours' time in service by the operator's fleet average time from takeoff to landing for the aircraft type.
(e) Upon request of the operator, an FAA maintenance inspector, subject to prior approval of the Chief, Aircraft Engineering Division, FAA Western Region, may adjust the repetitive inspection intervals specified in this AD to permit compliance at an established inspection period of the operator if the request contains substantiating data to justify the increase for such operator.
(Lockheed Service Bulletin 88/SB-612 dated February 14, 1964, covers this same subject).
This directive effective July 30, 1965.
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2000-11-11: This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 777-200 series airplanes, that requires one-time inspections to detect cracking of the aft wheel well bulkhead, corrective actions, if necessary, and modification of the aft wheel well bulkhead. For certain airplanes, this AD also requires a one-time visual inspection to detect excess sealant covering the outer flange of the side fitting and lower chord and splice area of the aft wheel well bulkhead, and corrective actions, if necessary. This amendment is prompted by a report indicating that numerous fatigue cracks were found in the aft wheel well bulkhead. The actions specified by this AD are intended to prevent fatigue cracking of the aft wheel well bulkhead, which could result in rapid in-flight decompression of the airplane.
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74-18-08: 74-18-08 TELEDYNE CONTINENTAL MOTORS: Amendment 39-1935. Applies to Teledyne Continental Model TSIO-360-C and TSIO-360-D engines.
Compliance required within the next 25 hours after the effective date of this AD, unless already accomplished.
To prevent fuel nozzle line leakage or breakage accomplish the following:
1. Carefully inspect the fuel nozzle lines for:
a. Chafing - where lines have rubbed together, rubbed other engines parts or have been rubbed by other items.
b. Kinks or sharp bends
c. Fuel stains at the ferrules
(lines must be replaced with airworthy components if any of the above discrepancies are found)
2. Install new clamps and brackets to prevent further chafing in accordance with Teledyne Continental Service Bulletin M74-5A or equivalent procedure approved by the Chief, Engineering and Manufacturing Branch, FAA Southern Region.
This amendment becomes effective August 30, 1974.
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77-17-05: 77-17-05 BELL: Amendment 39-3010 as amended by Amendment 39-3263. Applies to Models 204B, 205A-1, 212, 214B, and 214B-1 helicopters, certificated in all categories.
Compliance required as indicated.
To assure emergency exit latch pin engagement and to provide inspection holes for each exit retractable pin, accomplish the following:
(a) Within 100 hour's time in service after the effective date of this AD, accomplish the following one-time inspection and modification unless already accomplished.
(1) Inspect each exit internal and external handle cover installation and determine that NAS 43DD3-8 spacers, .12 inches long, are installed as illustrated in Bell Helicopter Textron Service Bulletin Nos. 204-77-2, 214-77-1, 212-77-11, or 205-77-9 or any revisions thereof.
(2) Add one-inch diameter inspection holes and provide a clear view of those holes through any interior lining in the right and left side passenger door assemblies in accordance with BHT Service Bulletin Nos. 205-77-6, 212-77-9, and 214-77-4 or later revision for the appropriate model helicopters.
For the Model 204B, locate the one-inch inspection hole center near the end of the fully-engaged latch pin, cut and debur the hole in the interior skin, and cut a one-inch hole in any interior lining, if installed.
(3) Label each of these inspection holes using stencils as noted in the service bulletins listed in paragraph (a)(2) of this AD; or use FAA approved equivalent placards, labels, or stencils located adjacent to each hole on the interior skin or lining, if installed.
(b) Within 100 hours' time in service after the effective date of this AD and thereafter at intervals not to exceed 300 hours' time in service from the last inspection, accomplish the following:
(1) Inspect the latch mechanism of each passenger exit and adjust as necessary to make each pin end flush with the exit frame edge, when the mechanism is in the fully unlatched position, as prescribed in Bell Helicopter Textron (BHT) Service Bulletin Nos. 205-76-12, 212-76-9, and 214-76-4 or later revision for the appropriate model helicopter. For the Model 204B, inspect and adjust the latch mechanism as noted but use appropriate procedures specified in Service Bulletin No. 205-76-12 or later revision.
(2) Inspect for and add as necessary a painted stripe around the cylinder part of each pin using white or other suitable color.
(c) Upon request of the operator, an FAA maintenance inspector, subject to prior approval of the Chief, Engineering and Manufacturing Branch, FAA, Southwest Region, may adjust the repetitive inspection intervals specified in this AD to permit compliance at an established inspection period of the operator if the request contains substantiating data to justify the increase for that operator.
(d) The manufacturer's instructions 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 the Service Manager, Bell Helicopter Textron, P.O. Box 482, Fort Worth, Texas 76101. These documents may also be examined at the Office of the Regional Counsel, Southwest Region, FAA, 4400 Blue Mound Road, Fort Worth, Texas, and at FAA Headquarters, 800 Independence Avenue, S.W., Washington, D.C., and at the Southwest Regional Office in Fort Worth, Texas.
(e) Emergency exit designs approved by the FAA that do not have a latch mechanism and latch pins to secure or release the exit are excluded from the applicability of this AD.
NOTE: STC SH2769SW has such an exit design.
Amendment 39-3010 became effective August 19, 1977.
This amendment 39-3263 becomes effective July 17, 1978.
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2015-13-03: We are adopting a new airworthiness directive (AD) for all Przedsiebiorstwo Doswiadczalno-Produkcyjne Szybownictwa ``PZL-Bielsko'' Model SZD-50-3 ``Puchacz'' sailplanes. This AD results from mandatory continuing airworthiness information (MCAI) issued by an aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as detachment of the rudder cable fitting block from the fuselage. We are issuing this AD to require actions to address the unsafe condition on these products.
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2015-13-02: We are adopting a new airworthiness directive (AD) for certain Bombardier, Inc. Model DHC-8-400 series airplanes. This AD was prompted by reports of corrosion in the low-rate discharge tubes of the fire protection system leading to the forward baggage compartment, and perforation of one or more tubes. This AD requires repetitive checks for leakage of the discharge tubes of the fire protection system. This AD also mandates eventual replacement of all existing aluminum tube assemblies with new, improved corrosion-resistant stainless steel tube assemblies. We are issuing this AD to prevent perforation of the low- rate discharge tubes, which could result in insufficient fire extinguishing agent reaching the forward baggage compartment in the event of a fire, which could result in damage to the airplane and injury to the occupants.
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2000-11-14: This document adopts a new airworthiness directive (AD) that applies to all Pilatus Aircraft Ltd. (Pilatus) Models PC-12 and PC-12/45 airplanes that are equipped with pneumatic deicing boots. This AD requires you to revise the Airplane Flight Manual (AFM) to include requirements for activation of the airframe pneumatic deicing boots. This AD is the result of reports of in-flight incidents and an accident (on airplanes other than the affected Pilatus airplanes) that occurred in icing conditions where the airframe pneumatic deicing boots were not activated. The Pilatus Models PC-12 and PC-12/45 airplanes have a similar type design (as it relates to airframe pneumatic ice boots) to the incident and accident airplanes. The actions specified by this AD are intended to assure that flightcrews activate the pneumatic wing and tail deicing boots at the first signs of ice accumulation. This action will prevent reduced controllability of the aircraft due to adverse aerodynamic effects of ice adhering to the airplane prior to the first deicing cycle
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