The U.S. aircraft register, updated daily
FAA orders · airworthiness directive · historical

2006-12-24: Five-link forward mount assembly

FAA order 2006-12-24 is an airworthiness directive in force since July 21, 2006. The FAA's subject line: Five-link forward mount assembly. It names the General Electric CF6-45A2, General Electric CF6-50C, General Electric CF6-50C2, General Electric CF6-80 series, General Electric CF6-80A, General Electric CF6-80A2 engines: about 263 aircraft on the U.S. register today across them, though an order usually covers particular versions or serial numbers rather than every one. System: engine.

What it applies to as the FAA lists it

Kind of product
Engine
Makes
General Electric Company
Models
CF6-45A, CF6-45A2, CF6-50A, CF6-50C, CF6-50C1, CF6-50C2, CF6-50C2B, CF6-50C2D, CF6-50CA, CF6-50E, CF6-50E1, CF6-50E2, CF6-50E2B, CF6-80A, CF6-80A1, CF6-80A2, CF6-80A3
Engine series
General Electric CF6-45A2 1 aircraft
General Electric CF6-50C 1 aircraft
General Electric CF6-50C2 10 aircraft
General Electric CF6-80 series 237 aircraft
General Electric CF6-80A 9 aircraft
General Electric CF6-80A2 5 aircraft

Dates and paperwork

In force since
July 21, 2006
Published
June 16, 2006 (signed June 8, 2006)
Docket
95-ANE-10-AD
Replaces
95-17-15
Replaced by
2011-23-04
Status
Historical
The FAA's document
Read the order on the FAA's site

The FAA's summary their words, unchanged

The FAA is superseding an existing airworthiness directive (AD) for General Electric Company (GE) CF6-45/-50 series turbofan engines. That AD currently requires an initial and repetitive on-wing visual inspection of the side links of the five-link forward mount assembly for cracks, and replacement of the side links and pylon attachment bolts and inspection of the fail-safe bolt and platform lug if the side links are cracked. That AD also requires a shop-level refurbishment of the side links as a terminating action to the on-wing inspection program. This ad requires inspecting and refurbishing the side link at every exposure of the side link. This AD also requires the same actions on certain part number side links installed on CF6-80A turbofan engines. This AD results from a report of a cracked side link. We are issuing this AD to prevent failure of the side links and possible engine separation from the airplane.

The order itself the regulatory text, as published

Show the full text (2,725 characters)
2006-12-24 General Electric Company: Amendment 39-14650. Docket No. 95-ANE-10-AD. Effective Date (a) This AD becomes effective July 21, 2006. Affected ADs (b) This AD supersedes AD 95-17-15, Amendment 39-9346. Applicability (c) This AD applies to General Electric (GE) CF6-45/-50 and CF6- 80A turbofan engines with left-hand side links part numbers (P/Ns) 9204M94P01, 9204M94P03, and 9346M99P01, and right-hand side links, P/Ns 9204M94P02, 9204M94P04, and 9346M99P02, installed on the five- link forward engine mount assembly (also known as Configuration 2). These engines are installed on, but not limited to, Boeing DC10-15, DC10-30, 767, and 747 series airplanes and Airbus Industrie A300 and A310 series airplanes. Unsafe Condition (d) This AD results from a report of a cracked side link. We are issuing this AD to prevent failure of the side links and possible engine separation from the airplane. Compliance (e) You are responsible for having theactions required by this AD performed at every exposure of the side link. Inspecting and Refurbishing the Side Links (f) Inspect and refurbish each side link at every exposure of the side links. Use the following GE Aircraft Engines (GEAE) service bulletins (SBs): (1) For CF6-45/-50 series engines, use 3.A. through 3.E. of the Accomplishment Instructions of GEAE SB CF6-50 S/B 72-1255, dated January 26, 2005. (2) For CF6-80A series engines, use 3.A. through 3.E. of the Accomplishment Instructions of GEAE SB CF6-80A S/B 72-0797, dated January 26, 2005. Definition of Exposure of Side Link (g) A side link is exposed when one or more bolts that attach the side links to the fan frame--front high pressure compressor case are removed, or when the bolt attaching the side link to the mount platform is removed. Alternative Methods of Compliance (h) The Manager, Engine Certification Office, has the authority to approve alternative methods of compliance for this AD if requested using the procedures found in 14 CFR 39.19. Material Incorporated by Reference (i) You must use General Electric Aircraft Engines Service Bulletins CF6-50 S/B 72-1255, dated January 26, 2005, and CF6-80A S/ B 72-0797, dated January 26, 2005 to perform the actions required by this AD. The Director of the Federal Register approved the incorporation by reference of these service bulletins in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. You can get a copy of this service information from General Electric Aircraft Engines, CF6 Distribution Clerk, Room 132, 111 Merchant Street, Cincinnati, OH 45246, or at the Office of the Federal Register, 800 North Capitol Street, NW., Suite 700, Washington, DC. Related Information (j) None.

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/2006-12-24.json · aircraft systems.