FAA orders · airworthiness directive · current

2002-01-30: Main Gearbox Magnet Plug

FAA order 2002-01-30 is an airworthiness directive in force since February 19, 2002. The FAA's subject line: Main Gearbox Magnet Plug. It names Aerospatiale SA315, S N I A S SE 3130, Sud Aviation SA 318: about 34 aircraft on the U.S. register today across them, though an order usually covers particular versions or serial numbers rather than every one. System: airframe structure.

What it applies to as the FAA lists it

Kind of product: Aircraft
Makes: Airbus Helicopters
Models: SA 3180-Alouette Astazou, SA 318B-Alouette Astazou, SA 318C-Alouette Astazou, SA.315B Alouette III, SA.316B Alouette III, SA.316C Alouette III, SA.319B Alouette III, SE 3130-Alouette II, SE 313B-Alouette II, SE.3160 Alouette III
On this site: Aerospatiale SA315 22 registered
S N I A S SE 3130 7 registered
Sud Aviation SA 318 5 registered

Dates and paperwork

In force since: February 19, 2002
Published: February 1, 2002 (signed January 22, 2002)
Docket: 2001-SW-38-AD
Status: Current
The FAA's document: Read the order on the FAA's site

The FAA's summary their words, unchanged

This amendment adopts a new airworthiness directive (AD) for Eurocopter France (ECF) Model SE 3130, SE 313B, SA 315B, SE 3160, SA 316B, SA 316C, SA 3180, SA 318B, SA 318C, and SA 319B helicopters with a certain main gearbox (MGB) installed. This action requires inspecting the magnetic plug for magnetic particles at specified intervals in addition to the MGB inspections currently required. This AD also requires, within 50 hours time-in-service (TIS), dye-penetrant inspecting the MGB bevel gear for a crack, and if a crack is found, replacing the cracked bevel gear with an airworthy bevel gear before further flight. This amendment is prompted by an MGB failure due to a cracked bevel gear. This condition, if not corrected, could result in failure of the MGB, loss of the main rotor drive, and subsequent loss of control of the helicopter.

The order itself the regulatory text, as published

Show the full text (3,191 characters)

2002-01-30  Eurocopter France: Amendment 39-12625. Docket No. 20.1-SW-38-AD. 

	Applicability: Model SE 3130, SE 313B, SA 315B, SE 3160, SA 316B, SA 316C, SA 3180, SA 318B, SA 318C, and SA 319B, helicopters with a main gearbox (MGB), part number 319A62-00-000.4 with serial number M1242, M2194, M2516, NT3488, NT3563, 3-2888, 3-3091, or 3-11336, installed, certificated in any category. 

	Note 1: This AD applies to each helicopter identified in the preceding applicability provision, regardless of whether it has been otherwise modified, altered, or repaired in the area subject to the requirements of this AD. For helicopters that have been modified, altered, or repaired so that the performance of the requirements of this AD is affected, the owner/operator must request approval for an alternative method of compliance in accordance with paragraph (d) of this AD. The request should include an assessment of the effect of the modification, alteration, or repair on the unsafe condition addressed by this AD; and if the unsafe condition has not been eliminated, the request should include specific proposed actions to address it. 

	Compliance: Required as indicated, unless accomplished previously. 

	To prevent failure of the MGB due to a cracked bevel gear, loss of the main rotor drive, and subsequent loss of control of the helicopter, accomplish the following: 

	(a) At intervals not to exceed 10 hours time-in-service (TIS), inspect the MGB magnet plug for metal particles. This 10-hour inspection is in addition to those currently required by the maintenance manual. 

	(b) Within 50 hours TIS, dye-penetrant inspect both faces of the MGB bevel gear in the coupling area of the bevel gear shaft and in the coupling area of the bevel gear housing for a crack. If a crack is found, replace the unairworthy part with an airworthy part before further flight. 

	Note 2: Eurocopter France Alert Service Bulletins 01.32 and 01.67, both dated July 18, 2001, pertain to the subject of this AD. 

	(c) Completing the dye-penetrant inspection required by paragraph (b) of this AD and finding no cracks or replacing the bevel gear with an airworthy bevel gear is terminating action for the requirements of this AD. 

	(d) 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, Regulations Group, Rotorcraft Directorate, FAA. Operators shall submit their requests through an FAA Principal Maintenance Inspector, who may concur or comment and then send it to the Manager, Regulations Group. 

	Note 3: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Regulations Group. 

	(e) Special flight permits may be issued in accordance with 14 CFR 21.197 and 21.199 to operate the helicopter to a location where the requirements of this AD can be accomplished. 

	(f) This amendment becomes effective on February 19, 2002. 

	Note 4: The subject of this AD is addressed in Direction Generale De L'Aviation Civile (France) ADs 2001-149-044(A) R1, 2001-178-058(A) R1, and 2001-179-061(A) R1, all dated August 8, 2001.

Source: FAA Dynamic Regulatory System, airworthiness directives. The FAA's document is the authority; the register counts are this site's, from the FAA register of October 7, 2026. Connections as data: /graph/directive/2002-01-30.json · aircraft systems.