AD 2003-12-08

Applicability: This airworthiness directive (AD) is applicable to General Electric Company (GE) CF6-80A1/A3 and CF6-80C2A PMC series turbofan engines. These engines are installed on, but not limited to Airbus Industrie A300-600 and A310 series airplanes.

Note 1:

This AD applies to each engine identified in the preceding applicability provision, regardless of whether it has been modified, altered, or repaired in the area subject to the requirements of this AD. For engines 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 (k) 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: Compliance with this AD is required as indicated, unless already done. To prevent inadvertent fan reverser deployment, which, if it occurred in-flight, could result in loss of control of the airplane, do the following:

(a) For GE CF6-80A1/A3 series engines, perform one of the following no later than 1,400 flight hours time-since-new (TSN) or 600 flight hours time-in-service (TIS) after the effective date of this AD, whichever occurs later:

(1) Perform the directional pilot valve (DPV) pressure switch moisture purge, in accordance with Paragraph 3.C. of the Accomplishment Instructions of Middle River Aircraft Systems Alert Service Bulletins (ASBs) CF6-80A1/A3 SB 78A4030, dated April 4, 2002, or CF6-80A1/A3 SB 78A4030, Revision 1, dated August 23, 2002, or

(2) Replace the DPV assembly with a serviceable assembly, or

(3) Deactivate the thrust reverser. The DPV must be replaced with a serviceable assembly within 10 days after deactivation. Information on deactivating the thrust reverser can be found in the applicable Aircraft Maintenance Manual (AMM).

(b) After each purge or replacement done in accordance with paragraph (a)(1), (a)(2), or (a)(3) of this AD, perform an operational check of the fan reverser in accordance with Paragraph 3.E. of the Accomplishment Instructions of ASBs CF6-80A1/A3 SB 78A4030, dated April 4, 2002, or CF6-80A1/A3 SB 78A4030, Revision 1, dated August 23, 2002.

(c) Thereafter, for GE CF6-80A1/A3 series engines, at intervals not to exceed 1,400 hours TIS since the last pressure switch purge or replacement of the DPV assembly, perform one of the following:

(1) Perform the DPV pressure switch moisture purge, in accordance with Paragraph 3.C. of the Accomplishment Instructions of Middle River Aircraft Systems ASBs CF6-80A1/A3 SB 78A4030, dated April 4, 2002, or CF6-80A1/A3 SB 78A4030, Revision 1, dated August 23, 2002, or

(2) Replace the DPV assembly with a serviceable assembly, or

(3) Deactivate the thrust reverser. The DPV must be replaced with a serviceable assembly within 10 days after deactivation. Information on deactivating the thrust reverser can be found in the applicable AMM.

(d) After each purge or replacement done in accordance with paragraph (c)(1), (c)(2), or (c)(3) of this AD, perform an operational check of the fan reverser in accordance with Paragraph 3.E. of the Accomplishment Instructions of ASBs CF6-80A1/A3 SB 78A4030, dated April 4, 2002, or CF6-80A1/A3 SB 78A4030, Revision 1, dated August 23, 2002.

(e) For GE CF6-80C2A1/A2/A3/A5/A8 series engines, perform one of the following no later than 1,400 flight hours TSN or 600 flight hours TIS after the effective date of this AD, whichever occurs later:

(1) Perform the DPV pressure switch moisture purge, in accordance with Paragraph 3.C. of the Accomplishment Instructions of Middle River Aircraft Systems ASBs CF6-80C2A PMC SB 78A1118, dated April 4, 2002, or CF6-80C2A PMC SB 78A1118, Revision 1, dated August 23, 2002, or

(2) Replace the DPV assembly with a serviceable assembly, or

(3) Deactivate the thrust reverser. The DPV must be replaced with a serviceable assembly within 10 days after deactivation. Information on deactivating the thrust reverser can be found in the applicable AMM.

(f) After each purge or replacement done in accordance with paragraphs (e)(1), (e)(2), or (e)(3) of this AD, perform an operational check of the fan reverser, in accordance with Paragraph 3.E. of the Accomplishment Instructions ASBs CF6-80C2A PMC SB 78A1118, dated April 4, 2002, or CF6-80C2A PMC SB 78A1118, Revision 1, dated August 23, 2002.

(g) Thereafter, for GE CF6-80C2A1/A2/A3/A5/A8 series engines, perform one of the following at intervals not to exceed 1,400 hours TIS since the last pressure switch purge or replacement of the DPV assembly:

(1) Perform the DPV pressure switch moisture purge, in accordance with Paragraph 3.C. of the Accomplishment Instructions of Middle River Aircraft Systems ASBs CF6-80C2A PMC SB 78A1118, dated April 4, 2002, or CF6-80C2A PMC SB 78A1118, Revision 1, dated August 23, 2002, or

(2) Replace the DPV assembly with a serviceable assembly, or

(3) Deactivate the thrust reverser. The DPV must be replaced with a serviceable assembly within 10 days after deactivation. Information on deactivating the thrust reverser can be found in the applicable AMM.

(h) After each purge or replacement done in accordance with paragraphs (g)(1), (g)(2), or (g)(3) of this AD, perform an operational check of the fan reverser, in accordance with Paragraph 3.E. of the Accomplishment Instructions of ASBs CF6-80C2A PMC SB 78A1118, dated April 4, 2002, or CF6-80C2A PMC SB 78A1118, Revision 1, dated August 23, 2002.

(i) For the purpose of this AD, a serviceable DPV assembly is an assembly that has:

(1) Accumulated zero time since new, or

(2) Passed the tests in the Middle River Aircraft Systems Component Maintenance Manual GEK 85007 (78-31-51), Revision No. 7 or later, Directional Pilot Solenoid Valve, Page Block 101, Testing and Troubleshooting, and that has zero flight hours TIS since passing the tests, or

(3) Been successfully purged according to paragraphs (a)(1), (c) (1), (e)(1) or (g)(1) of this AD immediately before installation on the fan reverser.

(j) If one or both thrust reversers are deactivated, then prior to further flight, revise the Limitations Section of the FAA-approved AFM to include the following:

“The takeoff performance on wet and contaminated runways with a thrust reverser(s) deactivated shall be determined in accordance with Airbus Flight Operations Telex (FOT) 999.0066/99, dated June 9, 1999, as follows:

For takeoff on wet runways, use performance data in accordance with paragraph 4.1.1 of the FOT.

For takeoff on contaminated runways, use performance data in accordance with paragraph 4.1.2 of the FOT.”

(1) Notwithstanding the provisions of the FAA approved A300-600 and A310 Master Minimum Equipment List (MMEL), dispatch with both thrust reversers deactivated, for the purposes of complying with this AD, is approved.

(2) Notwithstanding the provisions of the FAA Approved A300-600 and A310 MMEL, airplanes which have deactivated one or both thrust reversers in compliance with this AD, may not conduct operation on contaminated runways, as defined in Airbus Flight Crew Operating Manual Section 2.18.50, unless all components of the Main Wheel Brakes, Green and Yellow Brake Systems, Antiskid System, Ground Spoiler System, and all Spoiler and Speed Brake Surfaces, operate normally.

Note 2:

The “FCOM” referenced in Airbus FOT 999.0066/99, dated June 9, 1999, is Airbus Industrie Flight Crew Operating Manual (FCOM), Revision 27 for Airbus Model A310 series airplanes and Revision 22 for A300-600 series airplanes. [The revision number is indicated on the List of Effective Pages (LEP) of the FCOM.]

(k) 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, Engine Certification Office (ECO). Operators must submit their request through an appropriate FAA Principal Maintenance Inspector, who may add comments and then send it to the Manager, ECO.

Note 3:

Information concerning the existence of approved alternative methods of compliance with this airworthiness directive, if any, may be obtained from the ECO.

(l) Special flight permits may be issued in accordance with §§ 21.197 and 21.199 of the Federal Aviation Regulations (14 CFR 21.197 and 21.199) to operate the airplane to a location where the requirements of this AD can be done.

(m) The actions must be done in accordance with the following Middle River Aircraft Systems Alert Service Bulletins:

This incorporation by reference was approved by the Director of the Federal Register in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. Copies may be obtained from Middle River Aircraft Systems, Mail Point 46, 103 Chesapeake Park Plaza, Baltimore, MD, 21220-4295, telephone: (410) 682-0094; fax: (410) 682-0100. Copies may be inspected at the FAA, New England Region, Office of the Regional Counsel, 12 New England Executive Park, Burlington, MA; or at the Office of the Federal Register, 800 North Capitol Street, NW., suite 700, Washington, DC.

(n) This amendment becomes effective on July 23, 2003.