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2004-13-25: This amendment supersedes an existing airworthiness directive (AD), applicable to certain Airbus Model A330, A340-200, and A340-300 series airplanes, that currently requires repetitive inspections to check the play of the eye-end of the piston rod of the elevator servo- controls, and follow-on corrective actions if necessary. This amendment requires the replacement of certain elevator servo-controls with new, improved servo-controls. The actions specified by this AD are intended to detect and correct excessive play of the eye-end of the piston rod of the elevator servo-controls, which could result in failure of the elevator servo-control. This action is intended to address the identified unsafe condition.
DATES: Effective August 13, 2004.
The incorporation by reference of certain publications, as listed in the regulations, is approved by the Director of the Federal Register as of August 13, 2004.
The incorporation by reference of certain other publications, aslisted in the regulations, was approved previously by the Director of the Federal Register as of July 20, 2000 (65 FR 37476, June 15, 2000).
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48-11-04: 48-11-04 REPUBLIC: Applies to Model RC-3 Aircraft.
Compliance required by April 15, 1948.
To provide security for the hydraulic pump handle attachment, the four self-locking nuts now used should be replaced by three AN 310-4 and one AN 310-5 castle nuts and cotters. The fulcrum bolt is already drilled for a cotter. The present clevis bolts may be drilled for the cotter or may be replaced by two AN 24-17 and one AN 24-13 clevis bolts.
(Republic Service Bulletin No. 22 covers this same subject.)
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2022-02-19: The FAA is adopting a new airworthiness directive (AD) for certain Airbus Helicopters Deutschland GmbH (AHD) Model EC135P1, EC135P2, EC135P2+, EC135P3, EC135T1, EC135T2, EC135T2+, and EC135T3 helicopters. This AD was prompted by a report of restricted collective lever movement caused by entanglement of the emergency flashlight strap with the cargo hook emergency release lever, causing the emergency flashlight to leave its seat. This AD requires replacing each affected emergency flashlight with a serviceable part, 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.
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48-50-03: 48-50-03 MARTIN: Applies to Model 202 Aircraft.
Compliance required prior to reinstalling autopilot servo control systems.
Provide guards at joints of the stabilizer and wing flap torque tube systems in accordance with, or equivalent to, Martin Service Bulletin No. 72, dated October 22, 1948.
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43-07-01: 43-07-01 FAIRCHILD: (Was Service Note 2 of AD-724-2.) Applies to M-62 Series Aircraft.
At each periodic inspection, examine the wing center-section front and rear spars for wood deterioration and weakened glue joints due to moisture accumulation. (Method of inspection and repair, if necessary, are covered in Fairchild Service Maintenance Bulletin 45-62- 1, dated March 10, 1945.)
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2022-03-10: The FAA is adopting a new airworthiness directive (AD) for certain Airbus SAS Model A350-941 and -1041 airplanes. This AD was prompted by a report indicating that during maintenance, a fuse pin retaining the main landing gear support structure (MLGSS) was found incorrectly engaged in the trunnion block and improperly secured with the associated retaining pin, due to incorrect installation during assembly. This AD requires inspecting the fuse pins and associated retaining pins of the MLGSS for such discrepancies, and corrective action if necessary, 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.
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2004-14-10: This amendment supersedes an existing airworthiness directive (AD), applicable to certain McDonnell Douglas Model MD-11 and -11F airplanes, that currently requires, among other actions, replacing the ground support bracket(s); and rerouting the ground cables of the galley external power and main external power, as applicable. This amendment requires replacing ground support brackets with new brackets, and replacing ground cables of the galley external power and main external power with new cables; as applicable. This amendment also requires an inspection to detect the presence of a fillet seal at the ground brackets and to detect excessive length and correct terminations of the ground cables of the galley and main external power, as applicable; and corrective actions if necessary. The actions specified by this AD are intended to prevent arcing and heat damage to the attachment points of the main external and galley power receptacle ground wire, insulation blankets outboard andaft of the receptacle area, and adjacent power cables, which could result in smoke and fire in the forward cargo compartment. This action is intended to address the identified unsafe condition.
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2022-02-08: The FAA is adopting a new airworthiness directive (AD) for all Leonardo S.p.a. Model AB412 and AB412 EP helicopters. This AD was prompted by a report that certain oil and fuel check valves are susceptible to cracking. This AD requires determining whether the affected oil and fuel check valves are installed, visually inspecting the oil and fuel check valves for any crack, and depending on the inspection results, removing certain parts from service. This AD also requires removing affected parts from service and installing serviceable parts, and prohibits the installation of affected parts 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.
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47-10-34: 47-10-34 LOCKHEED: (Was Service Note 5 of AD-763-3.) Applies to All Model 49 Serials Up to and Including 2088.
(a) Revised exhaust system ball joint assemblies (Solar P/N CV-611 and CV-615-1 through CV-615-18, reworked in accordance with Solar E. O. Nos. 16696 and 16697), as called for in LAC Service Bulletin 49/SB-93 and AD 47-10-15, above, may continue to be used, provided a rigid inspection for condition is made in accordance with LAC Service Information Letter No. 42, except that the lowest periodic inspection interval listed on each operator's approved aircraft maintenance specification may be used instead of the 30-hour period referred to in the Lockheed Letter.
(b) The revised exhaust system ball joints described in part (a) of this Note may be reinstalled after completion of the 250-hour period referred to in LAC Service Information Letter No. 42, provided that each ball joint is disassembled as far as practicable at the end of these 250- hour periods and unsatisfactory parts are replaced. This 250-hour disassembly period may be increased upon application by an operator and approval by the FAA, provided the service record of the components used by the operator justified the increase requested.
(c) When the revised exhaust system ball joints, described in part (a) of this AD, are replaced by new type Solar ball joint parts, as listed in LAC Service Bulletin 49/SB-94, the overhaul period for exhaust system ball joints may be established as the same as the engine overhaul period approved for the operator involved. Intermediate inspections similar to those described in LAC Service Information Letter No. 42 shall be conducted on the new type ball joint assemblies at intervals as specified in the operator' approved aircraft maintenance specification.
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49-44-02: 49-44-02 CONVAIR: Applies to All Model 240 Series Aircraft.
To be accomplished not later than August 1, 1950.
Due to difficulties being located during the special inspections of the horizontal tail presently required by Airworthiness Directive 48-51-02, mandatory corrective action is now considered to be necessary. These difficulties include cracking of the left elevator leading edge ribs, cracking of the left elevator structure at the elevator flight tab hinge brackets, excessive wearing of the tab hinge pins, and loosening of the balance weights on the elevators and rudder. If allowed to progress, these difficulties could result in tail flutter or other hazardous conditions; therefore, it is considered necessary that the following rework be accomplished on all individual Convair Model 240 Series aircraft:
1. Install the revised elevator flight tab assembly, CVAC P/N 240-2210401-78.
(CVAC Service Bulletin No. 240-56A covers this same subject.)
2. Reinforcethe left elevator leading edge ribs outboard of Station 111.6, and strengthen the means of attaching the rudder and both left and right elevator balance weights.
(CVAC Service Bulletin No. 340-176A covers this same subject.)
3. Replace the present tab hinge pins and bushings with close tolerance bolts and bushings.
(CVAC Service Bulletin No. 240-205 covers this same subject.)
4. Reinforce the left elevator ribs at the flight tab hinge points.
(CVAC Service Bulletin No. 240-225 covers this same subject.)
5. Reinforce the left elevator leading edge ribs and the carry-through structure from leading edge ribs to the corresponding ribs aft of the spar, at Station 111.6 and inboard.
(CVAC Service Bulletin No. 240-268 covers reinforcement of the nose ribs. The portion of CVAC Service Bulletin No. 240-219 pertaining to Station 111.6 and inboard, covers reinforcement of the carry-through structures.)
6. Replace 4 of the 10 rivets in each of the inboard elevator hinge brackets which attach CVAC P/N 240-2110702 to the bracket assembly with 3/16 inch close tolerance steel bolts or steel rivets.
(CVAC Service Information Letter No. 415 covers this same subject and shows location of the specific rivets to be replaced.)
7. Between horizontal stabilizer station B. L. 50.50 and B. L. 59.50, add 4 rivets (AN 462-4-14 blind rivets may be used) to both the upper and lower surfaces. The rivet line should be 0.44 inch aft of the aft face of the vertical leg of the front spar cap (approximately 1/2 inch aft of the leading edge of the skin, i.e., 1/2 inch aft of the butt joint between the stabilizer leading edge skin and interspar skins). The rivets should be evenly spaced between B. L. 50.50 and B. L. 59.50 and not closer than 5/8 inch to any existing rivet.
(CVAC Service Difficulties and Parts Failures Report No. 245 covers this same subject.)
Although evidence indicates that horizontal tail failures will be materially reduced after incorporation of the above, some additional cracking may yet occur. Therefore, special inspections required by AD 48-51-02 must be continued until sufficient evidence of trouble-free operation has been supplied to the FAA to warrant discontinuance of these inspections.
This supersedes AD 49-17-01.
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