Airworthiness Directive · Amendment 39-16733 · Powerplant
Learjet Inc. Model 45 Airplanes
This AD applies to Learjet Inc. Model 45 airplanes; certificated in any category; serial numbers 45-005 through 45-405 inclusive, and 45-2001 through 45-2126 inclusive.
We are superseding an existing airworthiness directive (AD) for the products listed above. That AD currently requires, for certain airplanes, repetitive inspections for chafing and other damage of the case drain tube from the hydraulic pump case installed on the left-hand engine, and corrective action if necessary. That AD also requires, for all airplanes, repetitive inspections for discrepancies of the left engine's nacelle tubing, repetitive inspections for evidence of fluid leakage within the left engine accessory compartment, and corrective actions if necessary. This new AD also requires replacing the left engine fuel and hydraulic tubing and installing a tubing support channel, which terminates the repetitive inspections required in the existing AD. This new AD also removes airplanes from the applicability. This AD was prompted by reports of chafed hydraulic tubes in the left- hand engine. We are issuing this AD to prevent chafed hydraulic tubes in the left-hand engine and consequent hydraulic tube failure and uncontrolled loss of flammable fluid within the engine cowling, which could result in a fire in the engine nacelle and loss of control of the airplane.
You are responsible for having the actions required by this AD performed within the compliance times specified, unless the actions have already been done.
For airplanes having serial numbers identified in Table 1 of this AD: Within 50 flight hours after June 17, 2009 (the effective date of AD 2009-11-13), do a detailed inspection for chafing and other damage of the case drain tube from the hydraulic pump case installed on the left-hand engine, in accordance with the applicable service bulletin identified in Table 1 of this AD. If any damage is found, before further flight, reposition or replace the tube, as applicable, in accordance with the Accomplishment Instructions of the applicable service bulletin identified in Table 1 of this AD. Repeat the inspection thereafter at intervals not to exceed 150 flight hours until the modification required by paragraph (l) of this AD is done.
| For— | Use— |
|---|---|
| Serial numbers 45-005 through 45-313 inclusive (commonly referred to as “M45” airplanes) | Bombardier Alert Service Bulletin A45-29-15, dated December 26, 2006. |
| Serial numbers 45-2001 through 45-2063 inclusive (commonly referred to as “M40” airplanes) | Bombardier Alert Service Bulletin A40-29-03, dated December 26, 2006. |
Note 1: For the purposes of this AD, a detailed inspection is: “An intensive examination of a specific item, installation, or assembly to detect damage, failure, or irregularity. Available lighting is normally supplemented with a direct source of good lighting at an intensity deemed appropriate. Inspection aids such as mirror, magnifying lenses, etc., may be necessary. Surface cleaning and elaborate procedures may be required.”
Within 50 flight hours after June 17, 2009, do a detailed inspection for discrepancies of the left engine's nacelle tubing, in accordance with the applicable temporary revision (TR) identified in Table 2 of this AD. Discrepancies include damaged tubing, and inadequate clearance between any unsupported section of the tube or other tubing and surrounding components. If any discrepancy is found, before further flight, adjust the tubing and clamping or replace the tubing, as applicable, in accordance with the applicable TR identified in Table 2 of this AD. Repeat the inspection thereafter at intervals not to exceed 150 flight hours until the modification required by paragraph (l) of this AD is done.
| For— | Use— |
|---|---|
| Serial numbers 45-2001 through 45-4000 inclusive (commonly referred to as “M40” airplanes) | Learjet 40 TR 71-1, dated April 28, 2009, to the Learjet 40 Maintenance Manual MM-105. |
| Serial numbers 45-002 through 45-2000 inclusive (commonly referred to as “M45” airplanes) | Learjet 45 TR 71-1, dated April 28, 2009, to the Learjet 45 Maintenance Manual MM-104. |
(i) Concurrently with each inspection required by paragraph (h) of this AD, do a detailed inspection for evidence of engine oil, hydraulic fluid, or fuel leakage within the left engine accessory compartment, in accordance with the applicable maintenance manual section identified in Table 3 of this AD. If there is evidence of leakage: Before further flight, remove each plumbing clamp within the inspection areas specified in paragraphs (g) and (h) of this AD, and clean and remove all evidence of fluid leakage.
| For— | Use— |
|---|---|
| Serial numbers 45-002 through 45-2000 inclusive (commonly referred to as “M45” airplanes) | Section 71-00-00, “Powerplant—Maintenance Practices,” and Section 71-00-01, “Engine—Maintenance Practices,” of the Learjet 45 Maintenance Manual MM-104, Revision 47, dated March 30, 2009. |
| Serial numbers 45-2001 through 45-4000 inclusive (commonly referred to as “M40” airplanes) | Section 71-00-01, “Engine—Maintenance Practices,” of the Learjet 40 Maintenance Manual MM-105, Revision 15, dated March 30, 2009. |
If evidence of fluid leakage was found during any inspection required by paragraph (i) of this AD, or if inadequate clearance was found during any action required by paragraph (g) or (h) of this AD: Before further flight, replace each clamp associated with the fluid leakage or inadequate clearance with a new clamp, in accordance with the applicable maintenance manual identified in Table 3 of this AD.
As of June 17, 2009, no person may re-install, on any airplane, any plumbing clamp that has been removed in accordance with the requirements of paragraphs (g), (h), (i), or (j) of this AD.
Within 300 flight hours or 12 months after the effective date of this AD, whichever occurs first, do the actions specified in paragraphs (l)(1) and (l)(2) of this AD, in accordance with the Accomplishment Instructions of Bombardier Service Bulletin 40-71-04 (Model 45, serial numbers 45-2001 through 45-2126) or 45-71-7 (Model 45, serial numbers 45-005 through 45-405), both dated December 7, 2009, as applicable. Accomplishment of the requirements of paragraphs (l) and (m), as applicable, of this AD terminates the requirements of paragraphs (g), (h), (i), and (j) of this AD.
(1) Replace the left engine fuel and hydraulic tubing and install a tubing support channel using new parts.
(2) Do the inspections specified in paragraphs (l)(2)(i), (l)(2)(ii), (l)(2)(iii), and (l)(2)(iv) of this AD and all applicable corrective actions. Do all applicable corrective actions before further flight.
(i) A general visual inspection for galling of the fuel supply manifold assembly;
(ii) A general visual inspection for minimum clearance between the firewall fuel supply tube assembly and the engine firewall cutout;
(iii) A general visual inspection for minimum clearance between the lower nacelle hydraulic tube and hose assemblies; and
(iv) A general visual inspection for minimum clearance between the lower nacelle fuel tubes and flexible hoses.
(m) For airplanes having serial numbers 45-005 through 45-319, and 45-321, as identified in Bombardier Service Bulletin 45-71-5, dated February 13, 2007; and for airplanes having serial numbers 45-2001 through 45-2069, as identified in Bombardier Service Bulletin 40-71-02, dated February 13, 2007: Before or concurrently with accomplishing the requirements of paragraph (l) of this AD, do the applicable actions specified in paragraphs (m)(1), (m)(2), (m)(3), (m)(4), and (m)(5) of this AD, depending on airplane serial number and configuration, as specified in, and in accordance with, the Accomplishment Instructions of Bombardier Service Bulletin 45-71-5 (Model 45, serial numbers 45-005 through 45-319, and 45-321), dated February 13, 2007; or Bombardier Service Bulletin 40-71-02 (Model 45, serial numbers 45-2001 through 45-2069), dated February 13, 2007; as applicable. Do all applicable corrective actions before further flight. If, during any inspection required by paragraph (m)(3), (m)(4), or (m)(5) of this AD, it is determined that clearances are not met, before further flight, replace the tubing in accordance with the Accomplishment Instructions of Bombardier Service Bulletin 45-71-5, dated February 13, 2007; or Bombardier Service Bulletin 40-71-02, dated February 13, 2007; as applicable.
(1) Change the routing and clamping configuration of the engine and alternator wire harnesses and the starter/generator wire bundles.
(2) Do a detailed inspection for chafing damage of specific hydraulic tubes located within the left engine nacelle between the adjacent fuel tubes and to determine if there is interference between the fuel tubing and hydraulic tubing; secure hydraulic tubes with additional clamps, inspect adjacent fuel tubing for interference with the hydraulic tubing, replace the left engine hydraulic pump case drain tube on certain airplanes, and do all applicable corrective actions.
(3) Do a general visual inspection for clearance between the left engine hydraulic tubing with adjacent tubing, structure, and other components.
(4) Do a general visual inspection for clearance between the wire harnesses and the hydraulic and fuel tubing on the left engine.
(5) Do a general visual inspection for clearance between the wire harnesses and the hydraulic and fuel tubing on the right engine.
The aircraft, engines and makers this AD names, by the model designations in its text. A model listed here may still be outside the AD's serial ranges.
Aircraft
