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84-12-01 R1: 84-12-01 R1 HUGHES HELICOPTERS, INC. (HUGHES HELICOPTERS): Amendment 39-4877 as amended by Amendment 39-4937. Applies to Model 369D and 369E helicopters certificated in all categories.
Compliance is required prior to further flight, unless already accomplished.
To detect unapproved blades and prevent possible rotor blade failure in flight, accomplish the following:
For Hughes Helicopters, Inc., Model 369D and 369E helicopters with main rotor blades installed which have been procured from any source.
(a) To verify that the main rotor blades are of the proper Part Number (P/N) 369D21100 internal configuration, comply with the following:
(1) A coin tap test or equivalent test shall be used to identify the number of ribs in each blade. Carefully tap along the length of the blade, aft of the spar, from the tip end, using a heavy coin; e.g., U.S. quarter, half dollar, or equivalent. Note the number of ribs in the blade by the difference in sound. The proper P/N 369D21100 blade has 20 ribs, 1.5 inches apart, beginning 1.5 inches from the blade tip. The unapproved 369A1100 series blade has only four ribs, beginning 3 inches from the blade tip.
(2) The unapproved blade also has a painted over, flush plug installed to fill a 0.218- to 0.224-inch-diameter hole required in the trailing edge inboard end of all 369A1100 series blades. There is no such hole in the proper P/N 369D21100 blades. Inspect the blade for a filled hole in the trailing edge inboard end.
(b) If a blade has four ribs and a filled hole, an improper blade is installed. Replace with an airworthy proper P/N 369D21100 blade prior to further flight.
(c) Alternative inspections, modifications, or other actions which provide an equivalent level of safety to this AD may be used when approved by the Manager, Western Aircraft Certification Office, Hawthorne, California. The procedure specified in Hughes Service Information Letter DL-57 or EL-5, dated February 10, 1984, is an alternative.
NOTE: Hughes Service Information Letter No. DL-57 or EL-5 dated February 10, 1984, pertains to identification of improper blades.
Amendment 39-4877 became effective June 11, 1984.
This Amendment 39-4937 becomes effective October 24, 1984.
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2012-25-13: We are adopting a new airworthiness directive (AD) for certain The Boeing Company Model 747-100, 747-200B, 747-200C, 747-200F, 747- 300, 747-400, 747-400F, and 747SR series airplanes. This AD was prompted by reports of broken and damaged latch pin retention bolts and subsequent migration of the latch pins of the main deck side cargo door (MDSCD). This AD requires various repetitive inspections of the MDSCD latch pin fittings, measuring the latch pin, and related investigative and corrective actions if necessary. This AD also requires modifying the latch pin fittings and installing new latch pins and latch pin fasteners. We are issuing this AD to prevent loss of the cargo door and rapid depressurization of the airplane.
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98-16-22: This amendment adopts a new airworthiness directive (AD), applicable to certain Saab Model SAAB 2000 series airplanes, that requires a one-time inspection for cracking of the rear pressure bulkhead; and installation of a reinforcement angle on the rear pressure bulkhead; or repair, if necessary. 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 cracking of the rear pressure bulkhead, which could result in sudden loss of cabin pressure and the inability to withstand fail-safe loads.
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84-23-03: 84-23-03 ALEXANDER SCHLEICHER: Amendment 39-4945. Applies to Model ASK-21 sailplanes, all serial numbers, certificated in any category.
Compliance is required within the next 25 hours time in service after the effective date of this AD, unless already accomplished.
To comply with the requirements of Federal Aviation Regulation 21.29(a)(3), accomplish the following:
1. Remove the one placard in the German language fitted in the front and rear cockpit, and replace with new placards in the English language, in accordance with Alexander Schleicher ASK-21 Technical Note No. 14, dated May 16, 1984.
2. Remove and replace the following manual pages in accordance with Alexander Schleicher ASK-21 Technical Note No. 14, dated May 16, 1984:
a. In the Flight Manual, remove pages 2 (December 20, 1983) and 21 (March 9, 1983), and replace with pages 2 (May 16, 1984) and 21 (May 16, 1984).
b. In the Instructions for Continued Airworthiness, remove pages 2 (December 20, 1983) and 59 (March 9, 1983), and replace with pages 2 (May 16, 1984) and 59 (May 16, 1984).
3. Paragraph 2 of this AD may be accomplished by the pilot with logbook entry.
Upon request, an equivalent means of compliance with the requirements of this AD may be approved by the Manager, Brussels Aircraft Certification Office, AEU-10O, Europe, Africa, and Middle East Office, FAA, c/o American Embassy, 1000 Brussels, Belgium, telephone 513.38.30 extension 2710.
The Alexander Schleicher ASK-21 Technical Note No. 14, dated May 16, 1984, identified and described in this directive 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 these documents from the manufacturer may obtain copies upon request to Alexander Schleicher Segelflugzeubau, D-6416 Poppenhausen, Federal Republic of Germany. These documents may also be examined at the Office of the Regional Counsel, 12 New EnglandExecutive Park, Burlington, Massachusetts 01803.
This amendment becomes effective on November 14, 1984.
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98-16-25: This amendment supersedes an existing airworthiness directive (AD), applicable to certain Bombardier Model CL-600-2B19 (Regional Jet Series 100 and 200) airplanes, that currently requires repetitive inspections to detect discrepancies of the shock strut end caps and attachment pins of the main landing gear (MLG), and replacement of discrepant parts with new parts. It also requires a check for and replacement of certain pins that currently may be installed on some airplanes. This amendment adds a requirement for the installation of new, improved MLG shock strut upper and lower attachment pins, which constitutes terminating action for the repetitive inspections. This amendment also reduces the applicability of the existing AD by removing certain airplanes. 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 failure of attachment pins andthe attachment pin end caps, which could result in failure of the MLG.
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98-16-07: This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 767 series airplanes, that requires repetitive inspections to detect corrosion or plating cracks of the pin assemblies in the forward trunnion support of the main landing gear (MLG), and replacement of the pin assembly with a new assembly, if necessary. Such replacement, if accomplished, constitutes terminating action for the repetitive inspections. This amendment is prompted by reports indicating that these pin assemblies were found to have corroded as a result of plating cracks. The actions specified by this AD are intended to detect and correct such corrosion and plating cracks, which could cause breakage of these assemblies, and consequent collapse of the MLG.
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2012-27-01: We are adopting a new airworthiness directive (AD) for certain Rolls-Royce Deutschland Ltd & Co KG (RRD) Model Tay 620-15 turbofan engines. This AD requires a one-time inspection of the low-pressure compressor (LPC) fan blades and if erosion is found their replacement before further flight. This AD was prompted by evidence of excessive leading edge erosion of the LPC fan blades on certain Tay 620-15 engines. We are issuing this AD to prevent failure of the LPC fan blade, which could result in uncontained engine failure and damage to the airplane.
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66-19-03: 66-19-03 MARTIN: Amdt. 39-272 Part 39 Federal Register August 10, 1966. Applies to Model 404 Airplanes.
Compliance required as indicated.
To detect cracks in the main landing gear oleo cylinders, accomplish the following:
(a) Inspect main landing gear oleo cylinders, Martin P/N SE997712, in accordance with (c) within the next 50 hours' in service after the effective date of this AD, unless already accomplished within the last 100 hours' time in service, and at intervals not to exceed 150 hours' time in service from the last inspection.
(b) Inspect main landing gear oleo cylinders, except Martin P/N SE997712, in accordance with (c) within the next 50 hours' time in service after the effective date of this AD, unless already accomplished.
(c) Remove all grease, dirt, and loose paint in the area between the jury strut attach lugs of the right and left main landing gear oleo cylinders, and inspect each of these areas for cracks using an ultrasonic method or an FAA-approved equivalent method.
(d) If a crack is found during the inspection specified in (c), replace the cylinder with a part of the same part number inspected in accordance with this AD and found free of cracks or an equivalent approved by the Chief, Engineering and Manufacturing Branch, FAA Eastern Region, before further flight except that the airplane may be flown in accordance with FAR 21.197 to a base where the repair can be performed.
(e) Upon request of the operator, an FAA maintenance inspector, subject to prior approval of the Chief, Engineering and Manufacturing Branch, FAA Eastern Region, may adjust the repetitive inspection intervals specified in (a) to permit compliance at an established inspection period of the operator if the request contains substantiating data to justify the increase for that operator.
This directive effective August 19, 1966.
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98-16-03: This amendment adopts a new airworthiness directive (AD) that applies to certain SOCATA - Groupe AEROSPATIALE (Socata) Models TB9 and TB10 airplanes. This AD requires repetitively inspecting the wing front attachments on the wing and fuselage sides for cracks, and repetitively incorporating a certain modification kit (type of kit and time of incorporation depends on whether cracks are found during the inspection). This AD is the result of mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for France. The actions specified by this AD are intended to prevent structural failure of the wing front attachments caused by fatigue cracking, which could result in the wing separating from the airplane if the airplane is operated with cracked wing front attachments over an extended period of time.
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92-08-15: 92-08-15 MOONEY AIRCRAFT CORPORATION: Amendment 39-8266. Final copy of priority letter. Docket No. 92-CE-29-AD.
Applicability: Model M20J airplanes, serial numbers 24-3201, 24-3218 through 24-3238, 24-3240 through 24-3250, and 24-3252 through 24-3256, certificated in any category.
Compliance: Required as indicated, unless already accomplished.
To prevent rudder imbalance, which could lead to aerodynamic problems and loss of control of the airplane, accomplish the following:
(a) Prior to further flight after the effective date of this AD, accomplish the following:
(1) Fabricate a placard with the words "Maximum Gross Weight Reduced to 2,740 Pounds." Install this placard on the airplane instrument panel within the pilot's clear view.
(2) Insert a copy of this AD into the limitations section of the Airplane Flight Manual and operate the airplane accordingly.
(b) Within the next 15 hours time-in-service after the effective date of this AD, inspect the airplane to ensure that the rudder static balance is within the required limits in accordance with paragraphs 1. through 3. of the INSTRUCTIONS section of Mooney Aircraft Corporation Service Bulletin (SB) M20-252, dated April 6, 1992.
(c) If the rudder static balance falls outside the limits specified in Mooney Aircraft Corporation SB M20-252, prior to further flight, adjust the rudder balance weight in accordance with paragraphs 4. through 7. of the INSTRUCTIONS section of Mooney Aircraft Corporation SB M20-252, dated April 6, 1992.
(d) The placard and Airplane Flight Manual limitation required by paragraphs (a)(1) and (a)(2) of this AD are no longer required after compliance with paragraphs (b) and (c) of this AD as applicable.
(e) An alternative method of compliance or adjustment of the compliance times that provides an equivalent level of safety may be approved by the Manager, Airplane Certification Office, FAA, 4400 Blue Mound Road, Fort Worth, Texas 76193-0150. The request should be forwarded through an appropriate FAA Maintenance Inspector, who may add comments and then send it to the Manager, Fort Worth Airplane Certification Office.
NOTE: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Fort Worth Airplane Certification Office.
(f) The inspection and possible modification required by this AD shall be done in accordance with Mooney Aircraft Corporation Service Bulletin M20-252, dated April 6, 1992. 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 the Mooney Aircraft Corporation, P.O. Box 72, Kerrville, Texas 78029-0072. Copies may be inspected at the FAA, Central Region, Office of the Assistant Chief Counsel, Room 1558, 601 E. 12th Street, Kansas City, Missouri, or at the Office of the Federal Register, 1100 L Street, NW; Room8401, Washington, DC.
(g) This amendment becomes effective on June 30, 1992, to all persons except those persons to whom it was made immediately effective by priority letter AD 92-08-15, issued April 9, 1992, which contained the requirements of this amendment.
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