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2005-06-07: Directional pilot valve (DPV) assembly

FAA order 2005-06-07 is an airworthiness directive in force since April 25, 2005. The FAA's subject line: Directional pilot valve (DPV) assembly. It names the General Electric CF6-80 series, General Electric CF6-80C2A1, General Electric CF6-80C2A5, General Electric CF6-80C2A5F engines: about 249 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
CF6-80A1, CF6-80A3, CF6-80C2A1, CF6-80C2A2, CF6-80C2A3, CF6-80C2A5, CF6-80C2A5F, CF6-80C2A8
Engine series
General Electric CF6-80 series 238 aircraft
General Electric CF6-80C2A1 2 aircraft
General Electric CF6-80C2A5 3 aircraft
General Electric CF6-80C2A5F 6 aircraft

Dates and paperwork

In force since
April 25, 2005
Published
May 5, 2005 (signed March 9, 2005)
Docket
99-NE-41-AD
Replaces
99-18-19
Status
Current
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 GE CF6-80A1/A3 and CF6-80C2A series turbofan engines. That AD currently requires completing one of the following actions before further flight: Performing a directional pilot valve (DPV) pressure check for leakage, and, if necessary, replacing the DPV assembly with a serviceable assembly, or Replacing the DPV assembly with a serviceable assembly, or Deactivating the thrust reverser, and revising the FAA- approved airplane flight manual (AFM) to require applying performance penalties for certain takeoff conditions if a thrust reverser is deactivated. That AD also requires revising the Emergency Procedures Section of the FAA-approved AFM to include a flight crew operational procedure for use in the event of any indication of an in-flight thrust reverser deployment. This AD specifies the same requirements for leak checks, but increases the interval between required checks. This AD also removes the requirement to revise the Limitations Section and the Emergency Procedures Section of the applicable AFM when deactivating one or both thrust reversers. This AD results from Airbus Industrie, the airplane manufacturer, revising the master minimum equipment list (MMEL) to include procedures for operating the airplane with the thrust reversers deactivated, and revising the AFM to include procedures for emergency operation if the thrust reversers deploy while in flight. This AD also results from the engine manufacturer recommending extending the interval between inspecting or replacing the DPV. We are issuing this AD to prevent inadvertent thrust reverser deployment, which, if it occurs in-flight, could result in loss of control of the airplane.

The order itself the regulatory text, as published

Show the full text (9,071 characters)
2005-06-07 General Electric Company: Amendment 39-14015. Docket No. 99-NE-41-AD. Effective Date (a) This AD becomes effective April 25, 2005. Affected ADs (b) This AD supersedes AD 99-18-19, Amendment 39-11285. Applicability: (c) This AD applies to General Electric Company (GE) CF6-80A1/A3 and CF6-80C2A series turbofan engines. These engines are installed on, but not limited to, Airbus Industrie A300- 600 and A310 series airplanes. Unsafe Condition (d) This AD results from Airbus Industrie, the airplane manufacturer, revising the master minimum equipment list (MMEL) to include procedures for operating the airplane with the thrust reversers deactivated, and revising the Airplane Flight Manual (AFM) to include procedures for emergency operation if the thrust reversers deploy while in flight. This AD also results from the engine manufacturer recommending extending the interval between inspecting or replacing the directional pilot valve (DPV). We are issuing this AD to prevent inadvertent thrust reverser deployment, which, if it occurs in-flight, could result in loss of control of the airplane. Compliance (e) You are responsible for having the actions required by this AD performed within the compliance times specified, unless the actions have already been done. Credit for Initial Actions (f) Performing the initial actions using Middle River Aircraft Systems (MRAS) Alert Service Bulletin (ASB) No. CF6-80A1/A3 SB 78A4022, Revision 2, dated September 17, 2003, or earlier revision or MRAS ASB No. CF6-80C2A SB 78A1081, Revision 2, dated September 17, 2003, or earlier revision, satisfies the requirements of paragraphs (g) and (i) of this AD. GE CF6-80A1/A3 Series Engines Initial Actions (g) For GE CF6-80A1/A3 series engines, do either paragraph (g)(1) or (g)(2) of this AD. (1) Before further flight, perform a pressure check of the DPV for leakage. Use 2.B.(1) through 2.B.(12) of the Accomplishment Instructionsof MRAS ASB No. CF6-80A1/A3 SB 78A4022, Revision 2, dated September 17, 2003, and if necessary, do either of the following: (i) Replace the DPV assembly with a serviceable assembly and perform an operational check of the thrust reverser. Use 2.C.(1) through 2.C.(7) of the Accomplishment Instructions of MRAS ASB No. CF6-80A1/A3 SB 78A4022, Revision 2, dated September 17, 2003, or (ii) Deactivate the thrust reverser and do the following: (A) Replace the DPV with a serviceable DPV within 10 calendar days. (B) Perform an operational check of the thrust reverser. Use 2.C.(1) through 2.C.(7) of the Accomplishment Instructions of MRAS ASB No. CF6-80A1/A3 SB 78A4022, Revision 2, dated September 17, 2003. (2) Before further flight, replace the DPV assembly with a serviceable assembly, and perform an operational check of the thrust reverser. Use 2.C.(1) through 2.C.(7) of the Accomplishment Instructions of MRAS ASB No. CF6-80A1/A3 SB 78A4022, Revision 2, dated September17, 2003. GE CF6-80A1/A3 Series Engines Repetitive Actions (h) For GE CF6-80A1/A3 series engines, do either paragraph (h)(1) or (h)(2) of this AD within 1,400 hours time-in-service (TIS) since the last action. (1) Perform a pressure check of the DPV for leakage. Use 2.B.(1) through 2.B.(12) of the Accomplishment Instructions of MRAS ASB No. CF6-80A1/A3 SB 78A4022, Revision 2, dated September 17, 2003, and if necessary, do either of the following: (i) Replace the DPV assembly with a serviceable assembly and perform an operational check of the thrust reverser. Use 2.C.(1) through 2.C.(7) of the Accomplishment Instructions of MRAS ASB No. CF6-80A1/A3 SB 78A4022, Revision 2, dated September 17, 2003, or (ii) Deactivate the thrust reverser and do the following: (A) Replace the DPV with a serviceable DPV within 10 calendar days. (B) Perform an operational check of the thrust reverser. Use 2.C.(1) through 2.C.(7) of the Accomplishment Instructions of MRAS ASBNo. CF6-80A1/A3 SB 78A4022, Revision 2, dated September 17, 2003. (2) Replace the DPV assembly with a serviceable assembly, and perform an operational check of the thrust reverser. Use 2.C.(1) through 2.C.(7) of the Accomplishment Instructions of MRAS ASB No. CF6-80A1/A3 SB 78A4022, Revision 2, dated September 17, 2003. GE CF6-80C2A Series Engines Initial Actions (i) For GE CF6-80C2A series engines, do either paragraph (i)(1) or (i)(2) of this AD. (1) Before further flight, perform a pressure check of the DPV for leakage. Use 2.B.(1) through 2.B.(12) of the Accomplishment Instructions of MRAS ASB No. CF6-80C2A SB 78A1081, Revision 2, dated September 17, 2003, and if necessary, do either of the following: (i) Replace the DPV assembly with a serviceable assembly and perform an operational check of the thrust reverser. Use 2.C.(1) through 2.C.(5) of the Accomplishment Instructions of MRAS ASB No. CF6-80C2A SB 78A1081, Revision 2, dated September 17, 2003, or(ii) Deactivate the thrust reverser and do the following: (A) Replace the DPV with a serviceable DPV within 10 calendar days. (B) Perform an operational check of the thrust reverser. Use 2.C.(1) through 2.C.(5) of the Accomplishment Instructions of MRAS ASB No. CF6-80C2A SB 78A1081, Revision 2, dated September 17, 2003. (2) Before further flight, replace the DPV assembly with a serviceable assembly, and perform an operational check of the thrust reverser. Use 2.C.(1) through 2.C.(5) of the Accomplishment Instructions of MRAS ASB No. CF6-80C2A SB 78A1081, Revision 2, dated September 17, 2003. GE CF6-80C2A Series Engines Repetitive Actions (j) For GE CF6-80C2A series engines, do either (j)(1) or (j)(2) of this AD within 1,400 hours TIS since the last action. (1) Perform a pressure check of the DPV for leakage. Use 2.B.(1) through 2.B.(12) of the Accomplishment Instructions of MRAS ASB No. CF6-80C2A SB 78A1081, Revision 2, dated September 17, 2003, and if necessary, do either of the following: (i) Replace the DPV assembly with a serviceable assembly and perform an operational check of the thrust reverser. Use 2.C.(1) through 2.C.(5) of the Accomplishment Instructions of MRAS ASB No. CF6-80C2A SB 78A1081, Revision 2, dated September 17, 2003, or (ii) Deactivate the thrust reverser and do the following: (A) Replace the DPV with a serviceable DPV within 10 calendar days. (B) Perform an operational check of the thrust reverser. Use 2.C.(1) through 2.C.(5) of the Accomplishment Instructions of MRAS ASB No. CF6-80C2A SB 78A1081, Revision 2, dated September 17, 2003. (2) Replace the DPV assembly with a serviceable assembly, and perform an operational check of the thrust reverser. Use 2.C.(1) through 2.C.(5) of the Accomplishment Instructions of MRAS ASB No. CF6-80C2A SB 78A1081, Revision 2, dated September 17, 2003. Definition of Serviceable DPV Assembly (k) For the purpose of this AD, a serviceable DPV assembly is: (1) An assembly that has accumulated zero time in service, or (2) An assembly that has accumulated zero time in service after having passed the tests in the MRAS Component Maintenance Manual GEK 85007 (78-31-51), Revision No. 6 or later, Directional Pilot Valve, Page Block 101, Testing and Troubleshooting, or (3) An assembly that has been successfully leak checked using Paragraph 2.B. of the Accomplishment Instructions of MRAS ASB No. 78A4022, Revision 2, dated September 17, 2003, or earlier revision, or ASB No. 78A1081, Revision 2, dated September 17, 2003, or earlier revision, as applicable, immediately before installation on the airplane. Alternative Methods of Compliance (l) 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 (m) You must use the Middle River Aircraft Systems (MRAS) Alert Service Bulletins (ASB) listed in Table 1 of this AD to perform the actions required by this AD. The Director of the Federal Register approved the incorporation by reference of the documents listed in Table 1 of this AD in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. You can get a copy from Middle River Aircraft Systems, Mail Point 46, 103 Chesapeake Park Plaza, Baltimore, MD 21220, Attn: Product Support Engineering; telephone (410) 682-0098, fax (410) 682-0100. You can review copies at the FAA, New England Region, Office of the Regional Counsel, 12 New England Executive Park, Burlington, MA; or at the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, call 202-741-6030, or go to: http://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html . Table 1 follows: Table 1.--Incorporation by Reference Middle River Aircraft Systems ASB No. Page number(s) shown on the page Revisionlevel shown on the page Date shown on the page 78A4022, Total pages: 18 ALL 2 September 17, 2003. 78A1081, Total pages: 18 ALL 2 September 17, 2003. Related Information (n) 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 30, 2026. Connections as data: /graph/directive/2005-06-07.json · aircraft systems.