FAA orders · airworthiness directive · current

2003-24-12R1: Gearbox Pressure Tube

FAA order 2003-24-12R1 is an airworthiness directive in force since December 18, 2003. The FAA's subject line: Gearbox Pressure Tube. It names the Pratt & Whitney JT9D-3A, Pratt & Whitney JT9D-7, Pratt & Whitney JT9D series engines: about 18 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: Pratt & Whitney Division
Models: JT9D-3A, JT9D-7, JT9D-7A, JT9D-7AH, JT9D-7F, JT9D-7H, JT9D-7J
Engine series: Pratt & Whitney JT9D-3A 4 aircraft
Pratt & Whitney JT9D-7 1 aircraft
Pratt & Whitney JT9D series 13 aircraft

Dates and paperwork

In force since: December 18, 2003
Published: December 31, 2003 (signed December 23, 2003)
Docket: 2003-NE-52-AD
Replaces: 2003-24-12
Status: Current
The FAA's document: Read the order on the FAA's site

The FAA's summary their words, unchanged

The FAA is revising an existing airworthiness directive (AD) for Pratt & Whitney (PW) JT9D-3A, -7, -7A, -7F, -7H, -7AH, and -7J turbofan engines, with gearbox pressure tube, part number (P/N) 697896, and No. 4 bearing front pressure manifold, P/N 670663, installed. That AD currently requires a one-time visual inspection of the gearbox pressure tube and No. 4 bearing front pressure manifold and the attaching clamp assemblies for correct positioning and for wear and damage, and replacement if necessary. This ad requires the same actions. This AD results from the need to correct errors in depicted clamping to ensure that AD compliance can be achieved, and to relax the level of maintenance required, as an optional method, when inspecting the affected tubing for dents. We are issuing this AD to prevent engine fires caused by failed gearbox pressure tubes or failed No. 4 bearing front pressure manifolds.

The order itself the regulatory text, as published

Show the full text (4,444 characters)

2003-24-12R1 Pratt & Whitney: Amendment 39-13410. Docket No. 2003-NE-52-AD. Revises AD 2003-24-12, Amendment 39-13381. \n\nEffective Date \n\n\t(a) The effective date of this AD is the same as AD 2003-24-12, which is December 18, 2003. \n\nAffected ADs \n\n\t(b) This AD revises AD 2003-24-12. \n\nApplicability \n\n\t(c) This AD applies to Pratt & Whitney (PW) JT9D-3A, -7, -7A, -7F, -7H, -7AH, and -7J turbofan engines, with gearbox pressure tube, part number (P/N) 697896, and No. 4 bearing front pressure manifold, P/N 670663, installed. These engines are installed on, but not limited to, Boeing 747-100, -200B, -200C, and -200F airplanes. \n\nUnsafe Condition \n\n\t(d) This AD results from the need to correct errors in depicted clamping, to ensure that AD compliance can be achieved. The actions specified in this AD are intended to prevent engine fires caused by failed gearbox pressure tubes or failed No. 4 bearing front pressure manifolds. \n\nCompliance \n\n\t(e) You are responsible for having the actions required by this AD performed within 250 hours-in-service or at the next shop visit, whichever occurs first, after the effective date of this AD, unless the actions have already been done. \n\nOne-Time Visual Inspection of Clamp Assemblies \n\n\t(f) Visually inspect the clamp assemblies, P/Ns ST1594-06, ST1594-08, and ST1594-10, (see Figure 1 of this AD) that attach the gearbox pressure tube and the No. 4 bearing front pressure manifold to the engine. Replace clamp assemblies before further flight that are rejected by any of the following rejection criteria: \n\n\t(1) Cracks, wear, or distortion in clamp metal. \n\n\t(2) Clamp cushions that are worn, compacted, cracked, coming apart in chunks, deteriorated, or missing. A reddish powder found around the clamp is an indication of deterioration. \n\n\n\n\nVisual Inspection of Gearbox Pressure Tube and No. 4 Bearing Front Pressure Manifold \n\n\t(g) If one or more clamp assemblies are rejected as described in paragraph (f) ofthis AD, or out of position or missing (see Figure 1 of this AD), clean any debris and oil from the outer surface of the gearbox pressure tube and No. 4 bearing front pressure manifold and visually inspect the tube and manifold. Repair or replace the affected tube or manifold before further flight if it is rejected by any of the following rejection criteria: \n\n\t(1) Nicks, chafing, scratches, and or pitting 0.003 inch or greater in depth. \n\n\t(2) Dents within 0.25 inch of the ferrules or will not permit free passage of a ball having a minimum diameter of 80% of the tubing inner diameter. \n\n\t(3) Corrosion that is unable to be removed by a light polishing. \n\n\t(4) Tube or manifold is leaking oil. \n\n\t(5) As an option to the dent inspection method specified in paragraph (g)(2) of this AD, measure tube dent depth and use the following rejection criteria: \n\n\t(i) Dents in the gearbox pressure tube, P/N 697896, greater than 0.055-inch depth. \n\n\t(ii) Dents in the No. 4 bearing frontpressure manifold, P/N 670663, forward of the tee fitting, greater than 0.100-inch depth. \n\n\t(iii) Dents in the No. 4 bearing front pressure manifold, PN 670663, aft of the tee fitting, greater than 0.080-inch depth. \n\nGearbox Pressure Tube, No. 4 Bearing Front Pressure Manifold, and Clamp Assembly Positioning \n\n\t(h) Ensure that the gearbox pressure tube, No. 4 bearing front pressure manifold, and clamp assemblies are properly positioned, before further flight, as shown in Figure 1 of this AD. \n\n\t(i) Information on general inspection of these parts can be found in the Boeing 747 Aircraft Maintenance Manual, section 72-00-00, and in PW Standard Practices Manual, P/N 585005. \n\nReporting Requirements \n\n\t(j) Report within 30 calendar days of the inspection, the results that equal or exceed the reject criteria to: Engine Certification Office, FAA, Engine and Propeller Directorate, 12 New England Executive Park, Burlington, MA 01803-5299; telephone (781) 238-7189; fax (781) 238-7199. Reporting requirements have been approved by the Office of Management and Budget control number 2120-0056. \n\nAlternative Methods of Compliance \n\n\t(k) 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. \n\nMaterial Incorporated by Reference \n\n\t(l) None. \n\nRelated Information \n\n\t(m) 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/2003-24-12R1.json · aircraft systems.