FAA orders · airworthiness directive · current

2004-25-22: Engine induction system

FAA order 2004-25-22 is an airworthiness directive in force since January 28, 2005. The FAA's subject line: Engine induction system. It names Great Lakes 2: about 168 aircraft on the U.S. register today, 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: Aircraft
Makes: Great Lakes Aircraft Company, LLC (John Duncan)
Models: 2T-1A-1, 2T-1A-2
On this site: Great Lakes 2 168 registered

Dates and paperwork

In force since: January 28, 2005
Published: December 16, 2004 (signed December 7, 2004)
Docket: FAA-2004-18744
Replaces: 79-20-08
Status: Current
The FAA's document: Read the order on the FAA's site

The FAA's summary their words, unchanged

The FAA supersedes Airworthiness Directive (AD) 79-20-08, which applies to all Great Lakes Aircraft Company, LLC, (Great Lakes) Models 2T-1A-1 and 2T-1A-2 airplanes with a Lycoming IO-360-B1F6 or AIO-360-B1G6 engine installed. AD 79-20-08 currently requires you to inspect the engine induction system and the alternate air door for any signs of damage and repairing or replacing any damaged components. AD 79-20-08 also requires you to inspect the induction system for the presence of a drain fitting. If the drain fitting is blocked, restricted, or does not exist, AD 79-20-08 requires you to clear the fitting or drill a hole in the elbow at the fitting location. This AD is the result of the FAA inadvertently omitting Lycoming engine AEIO- 360-B1G6 from the applicability section of AD 79-20-08. Consequently, this AD retains the actions required in AD 79-20-08 and adds Lycoming engine AEIO-360-B1G6 to the applicability section. We are issuing this AD to prevent the aircraft inductionsystem from becoming blocked or restricted, which could result \nin engine failure. This failure could lead to loss of control of the airplane.

The order itself the regulatory text, as published

Show the full text (4,915 characters)

2004-25-22 Great Lakes Aircraft Company, LLC: Amendment 39-13910; Docket No. FAA-2004-18744; Directorate Identifier 2004-CE-24-AD; Supersedes AD 79-20-08; Amendment 39-3580. \n\nWhen Does This AD Become Effective? \n\n\t(a) This AD becomes effective on January 28, 2005. \n\nWhat Other ADs Are Affected by This Action? \n\n\t(b) This AD supersedes AD 79-20-08, Amendment 39-3580. \n\nWhat Airplanes Are Affected by This AD? \n\n\t(c) This AD affects all Model 2T-1A-1 and 2T-1A-2 airplanes that have a Lycoming IO-360-B1F6, AIO-360-B1G6, or AEIO-360-B1G6 engine installed and are certificated in any category. \n\nWhat Is the Unsafe Condition Presented in This AD? \n\n\t(d) This AD is the result of heat distortion, damage, and cracks found in the aircraft induction system on Lycoming IO-360-B1F6, AIO- 360-B1G6, and AEIO-360-B1G6 engines. The actions specified in this AD are intended to prevent the aircraft induction system from becoming blocked or restricted, which could result in engine failure. This failure could lead to loss of control of the airplane. \n\nWhat Must I Do To Address This Problem? \n\n\t(e) To address this problem, you must do the following: \n\n\n\nActions \nCompliance \nProcedures \n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n(1) Perform the following: \n(i) Visually inspect the aircraft induction system drain fitting located in the induction elbow below the fuel injector for blockage or restriction. \n(ii) If the hole is blocked or restricted in the weld area or not drilled through the elbow, open up the restricted hole or drill a hole in the elbow at the fitting location\nFor all affected airplanes: Inspect within the next 25 hours time-in-service (TIS) after January 28, 2005 (the effective date of this AD). Before further flight, modify the blocked or restricted aircraft induction system drain fitting. \nNot applicable. \n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n(2) Visually inspect the alternate air door for distortion, heat damage, andcracks. If any damage is found, repair or fabricate a new door following \nFigure 1, Figure 2, and Figure 3 in this AD. \nFor airplanes previously affected by AD 79-20-08: Initially inspect at the next scheduled inspection required by AD \n79-20-08 or within the next 25 hours TIS after January 28, 2005 (the effective date of this AD), whichever occurs \nlater. Repetitively inspect thereafter at intervals not to exceed 100 hours TIS. For airplanes not previously affected \nby AD79-20-08: Inspect within the next 25 hours TIS after January 28, 2005 (the effective date of this AD). Repetitively inspect thereafter at intervals not to exceed 100 hours TIS. For all affected airplanes: After each inspection, if damage is found during any inspection, before further flight, repair, replace the damaged alternate air door. \nNot applicable. \n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n(3) Visually inspect the aircraft induction system for cleanliness of the air filter, distortion, security, and damage from \nbackfire or induction system fire. If the air filter is dirty, if any distortion, damage, or lack of security is found, repair, replace or modify all affected components. \nFor airplanes previously affected by AD 79-20-08: Initially inspect at the next scheduled inspection required by AD \n79-20-08 or within the next 25 hours TIS after January 28, 2005 (the effective date of this AD), whichever occurs \nlater. Repetitively inspect thereafter at intervals not to exceed 100 hours TIS. For airplanes not previously affected \nby AD 79-20-08: Inspect within the next 25 hours TIS after January 28, 2005 (the effective date of this AD). Repetitively inspect thereafter at intervals not to exceed 100 hours TIS. For all affected airplanes: After each inspection, if damage is found during any inspection, before further flight, repair, replace or modify any damaged components. \nNot applicabale. \n\nMay I Request an Alternative Method of Compliance? \n\n\t(f) You may request a different method of compliance or a different compliance time for this AD by following the procedures in 14 CFR 39.19. Unless FAA authorizes otherwise, send your request to your principal inspector. The principal inspector may add comments and will send your request to the Manager, Denver Aircraft Certification Office, FAA. For information on any already approved alternative methods of compliance, contact Roger Caldwell, Aerospace Engineer, Denver ACO, FAA, 26805 E. 68th Ave., Rm 214 Denver, CO 80249-6361; telephone: (303) 342-1086; facsimile: (303) 342-1088. \n\nMay I Get Copies of the Documents Referenced in This AD? \n\n\t(g) You may view the AD docket at the Docket Management Facility; U.S. Department of Transportation, 400 Seventh Street, SW., Nassif Building, Room PL-401, Washington, DC 20590-001 or on the Internet at http://dms.dot.gov. The docket number is FAA-2004-18744.

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 5, 2026. Connections as data: /graph/directive/2004-25-22.json · aircraft systems.