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2009-25-09: We are adopting a new airworthiness directive (AD) for the specified Eurocopter France (Eurocopter) helicopters. This AD results from a mandatory continuing airworthiness information (MCAI) AD issued by the European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Community. The MCAI Emergency AD states that there has been a report of the failure of a flexible coupling on one of the main gearbox (MGB) inputs, which may be the result of loss of the tightening torque load, or insufficient tightening of the nuts on the bolts fixing the discs of the flexible coupling to its sliding and fixed hinges. This condition, if not corrected, could result in failure of the coupling discs, and if this condition develops on both the left-hand (LH) and right-hand (RH) MGB inputs, a complete loss of power to the transmission and subsequent loss of control of the helicopter.
80-13-09: 80-13-09 MCDONNELL DOUGLAS: Amendment 39-3811. Applies to McDonnell Douglas Model DC-10-10, -10F, -30, -30F and -40 Series Airplanes certificated in all categories utilizing Air Cruisers Part No. 24D30051 series passenger evacuation systems with the following serial numbers: \n\n\tLeft Hand Door: Air Cruisers Company P/N 24D30051 series, all serial numbers prior to S/N 1531, except 1508, 1510, 1511, 1515, 1519, 1521, 1523 and 1525. \n\n\tRight Hand Door: Air Cruisers Company P/N 24D30051 series, all serial numbers prior to S/N 1630, except 1605, 1611, 1613, 1615, 1619, 1621 and 1623. \n\n\tCompliance required within next eighteen (18) calendar months after the effective date of this AD, unless already accomplished. \n\n\tTo prevent improper deployment of the Air Cruisers Company emergency evacuation system due to delay in separation of the velcro tracking restraint device, accomplish the following: \n\n\ta.\tModify the affected evacuation system assemblies in accordance with Part 2, Accomplishment Instructions, of Air Cruisers Company Service Bulletin No. 25-75 dated January 24, 1980. \n\n\tb.\tSpecial flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate airplanes to a base for the accomplishment of modifications required by this AD. \n\n\tc.\tAlternative modifications or other actions which provide an equivalent level of safety may be used when approved by the Chief, Aircraft Engineering Division, FAA Western Region. \n\n\tThis amendment becomes effective August 30, 1980.
47-10-29: 47-10-29 LOCKHEED: (Was Mandatory Note 32 of AD-763-3.) Applies to All Model 49 Serials Prior to 2080 on Which Metal Ailerons Are Installed. Compliance required prior to April 1, 1947. Between aileron Stations 69.5 and 99.7, install drain holes in the lower aileron surface outboard of each rib and forward of each stringer (17 holes total). (LAC Service Bulletin 49/SB-214 covers this same subject.)
80-18-03: 80-18-03 PIPER (Ted Smith): Amendment 39-3900. Applies to Aerostar Model 601 and 601P series airplanes certificated in all categories. Compliance required as indicated, unless already accomplished. To prevent possible engine failure due to excessive lean fuel/air mixture, accomplish the following: (a) Within 30 days from the effective date of this AD, index and mark the left hand and right hand engine fuel pressure gauges with a yellow arc between the 12 psi and 18 psi range, and incorporate provisions in the Airplane Flight Manual Operations Limitations Section as follows: 1. In the Power Plant Instruments paragraph and under the Yellow ARC Caution column of the fuel pressure data add "12 -18 psi" 2. In the Fuel System Limitations paragraph add the statement "Fuel boost pump must be "ON" when fuel pressure indication is less than 18 psi and engine is operating above idle power." (b) Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate airplanes to a base for the accomplishment of the modifications required by this AD. (c) Alternative modifications or other actions which provide an equivalent level of safety may be used when approved by the Chief, Aircraft Engineering Division, FAA Western Region. This amendment becomes effective October 6, 1980.
80-19-10: 80-19-10 CESSNA: Amendment 39-3922. Applies to Model 335 (Serial Numbers 335-0001 thru 335-0054 and 335-0056) and Model 340A (Serial Numbers 340A0901 thru 340A0994 and 340A1002) airplanes certified in all categories. COMPLIANCE: Required as indicated unless the requirements of Paragraph B) have been previously accomplished. To prevent flight in adverse weather conditions with no means to supply electrical power to the deicer systems: A) Prior to further flight: 1. Install, and operate the airplane in accordance with, a temporary placard on the instrument panel just below the glareshield in the pilot's line of forward vision when seated in the left control seat which states, "Not Approved For Flight In Icing Conditions." 2. Install black electrician's tape or equivalent over the bottom portion of the airplane Operational Limits placard, which is located on the pilot's sun visor, to cover the wording "AND FLIGHTS INTO ICING CONDITIONS IF THE PROPER OPTIONAL EQUIPMENT IS INSTALLED AND OPERATIONAL." 3. Pull the propeller deice and optional heated windshield circuit breakers, if installed, and install a band around each breaker to prevent activating those circuits. B) Within 25 hours time-in-service after the effective date of the AD, perform the wiring inspection and accomplish the wiring change, if required, in accordance with Cessna Multi-engine Customer Care Service Information Letter ME80-31 dated July 18,1980. Make the prescribed entry in the airplane maintenance records. C) Remove the temporary placard, cover tape and circuit breaker bands specified in Paragraphs A)1., 2., and 3. when Paragraph B has been accomplished. D) Within seven days notify, in writing, the Chief, Aircraft Certification Program, Federal Aviation Administration, Room 238, Terminal Building No. 2299, Mid-Continent Airport, Wichita, Kansas 67209 of any incorrect wiring of the deicer buss found when complying with Paragraph B). One acceptable means of making these reports is Malfunction or Defect Report (FAA Form 8010-4). (Reporting approved by the Office of Management and Budget under OMB No. 04-R0174.) Failure to comply with this paragraph subjects owners/operators to agency enforcement action. E) The airplane may be flown in accordance with FAR 21.197 to a location where this AD may be accomplished. F) Any equivalent method of compliance with this Airworthiness Directive must be approved by the Chief, Aircraft Certification Program, Federal Aviation Administration, Room 238, Terminal Building No. 2299, Mid-Continent Airport, Wichita, Kansas 67209. This amendment becomes effective on September 29, 1980, to all persons except those to whom it has already been made effective by an airmail letter from the FAA dated September 4, 1980, and is identified as AD 80-19-10.
2009-24-22: We are adopting a new airworthiness directive (AD) for certain Learjet Model 45 airplanes. This AD requires inspecting the baggage bay door fire barrier seal for inconel mesh in the fire barrier seal material; for certain airplanes, inspecting the fiberglass doublers for presence of red Room Temperature Vulcanizing (RTV) sealant; and doing related investigative and corrective actions if necessary. This AD results from reports of incorrect external baggage door seal material and door seal sealant, as well as incorrect sealant on interior baggage panels used during manufacture of the airplane. We are issuing this AD to prevent the use of door seals and sealant that do not meet flammability requirements, which could result in an uncontrollable and undetected fire within the baggage compartment.
62-16-03: 62-16-03 LOCKHEED: Amdt. 461 Part 507 Federal Register July 12, 1962. Applies to All Models 1049-54, 1049B, 1049C, 1049D, 1049E, 1049F, 1049G, and 1049H Series Aircraft. Compliance required as indicated. As a result of corrosion found on the wing rear spar upper cap exposed surfaces which exceeded the negligible damage limits the following is required: (a) Within the next 700 hours' time in service after the effective date of this AD, unless already accomplished, inspect the exposed surfaces of the rear spar upper caps from wing Station 80 to wing Station 458 using a wood or micarta pick as a probe and a good light source to illuminate the area. (b) If no corrosion is found, coat the spar cap with zinc chromate primer. The aircraft may then be returned to service. (c) If corrosion damage is found on the exposed surfaces of the rear spar upper cap, remove enough rivets from the aft upper surface skin to allow lifting the skin for the purpose of inspecting the aftouter surface of the rear spar upper cap in accordance with (a). (d) Repair all corrosion damage in accordance with Lockheed Report 8882, figure 2- 25 and paragraph 1-67N, or FAA approved equivalent. If no corrosion is found on the aft outer surface of the rear spar upper cap, coat it with zinc chromate. (e) All rear spar upper caps which have been inspected and repaired in accordance with (a) through (d) shall be reinspected and repaired in accordance with (a) through (d) at periods thereafter not to exceed 5,000 hours' time in service or two calendar years, whichever occurs first. The first periodic reinspection of any rear spar upper cap which was inspected and repaired in the manner prescribed in (a) through (d) prior to the effective date of this AD, shall be accomplished within 5,000 hours' time in service or two calendar years, whichever occurs first, following the date of that inspection. (f) Upon request of the operator, and FAA maintenance inspector, subject to prior approval of the Chief, Engineering and Manufacturing Branch, 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 Field Service Letters FS/249582L dated November 4, 1960, and FS/250141L dated December 20, 1960, cover this same subject.) This directive effective August 13, 1962.
2007-15-06 R1: The FAA is revising an existing airworthiness directive (AD), which applies to all Airbus Model A318-111 and -112 series airplanes, and all Model A319, A320, and A321 series airplanes. That AD currently requires revising the Airworthiness Limitations section of the Instructions for Continued Airworthiness to incorporate new limitations for fuel tank systems. This AD clarifies the intended effect of the AD on spare and on-airplane fuel tank system components. This AD results from fuel system reviews conducted by the manufacturer. We are issuing this AD to prevent the potential of ignition sources inside fuel tanks, which, in combination with flammable fuel vapors, could result in a fuel tank explosion and consequent loss of the airplane. DATES: This AD is effective December 14, 2009. The Director of the Federal Register approved the incorporation by reference of a certain publication listed in the AD as of December 14, 2009. On August 28, 2007 (72 FR 40222, July 24,2007), the Director of the Federal Register approved the incorporation by reference of certain other publications listed in the AD. We must receive any comments on this AD by January 11, 2010.
2008-24-04: This amendment supersedes an existing airworthiness directive (AD) for the specified Eurocopter France (Eurocopter) model helicopters. That AD currently requires certain checks of the magnetic chip detector plug (chip detector) and the main gearbox (MGB) oil-sight glass, certain inspections of the lubrication pump (pump), and replacing the MGB and the pump with an airworthy MGB and pump, if necessary. Also, the AD requires that before a pump or MGB with any hours time-in-service (TIS) can be installed, it must meet the AD requirements. This AD adds all serial-numbered pumps to the applicability and requires using an improved procedure for detecting oil pump wear. This amendment is prompted by additional cases of MGB lubrication pump deterioration and a further investigation that determined that all serial-numbered pumps might be affected and the development of an improved procedure that is more accurate for detecting oil pump wear earlier. The actions specified by this AD areintended to implement improved procedures to detect a failing MGB oil pump, prevent failure of the MGB pump, seizure of the MGB, loss of drive to an engine and main rotor, and subsequent loss of control of the helicopter.
47-06-02: 47-06-02 GLOBE: (Was Mandatory Note 5 of AD-766-5.) Applies to Models GC-1A and GC-1B Aircraft Serial Numbers 3 to 408 Inclusive; 1004 to 1319 Inclusive; and 2001 to 2239 Inclusive. Compliance required prior to April 1, 1947. Replace the warning placard located at the landing gear emergency extension crank with a revised placard, Globe P/N 11-532-3735, having the added instruction: "Crank back to the full up position before the next retraction of the landing gear". Complete rewinding is necessary to prevent damage to the retraction system. (Globe Customer Service Maintenance Bulletin No. 6 covers this same subject.)