Airworthiness Directive · Amendment 39-15197 · Boeing Model 737-600, -700, -700C, -800, -900, and -900ER Series Airplanes
Boeing Model 737-600, -700, -700C, -800, -900, and -900ER Series Airplanes
Superseded. A later AD replaced this one: AD 2011-06-05. Comply with the one in force.
This AD applies to all Boeing Model 737-600, -700, -700C, -800, -900, and -900ER series airplanes, certificated in any category.
This document publishes in the Federal Register an amendment adopting airworthiness directive (AD) 2007-18-52 that was sent previously to all known U.S. owners and operators of Boeing Model 737- 600, -700, -700C, -800, -900, and -900ER series airplanes by individual notices. This AD requires repetitive detailed inspections of the slat track downstop assemblies to verify that proper hardware is installed, one-time torquing of the nut and bolt, and corrective actions if necessary. This AD is prompted by reports of parts coming off the main slat track downstop assemblies. We are issuing this AD to detect and correct loose or missing parts from the main slat track downstop assemblies, which could result in a fuel leak and consequent fire.
You are responsible for having the actions required by this AD performed within the compliance times specified, unless the actions have already been done.
Note 1: Paragraph (f) of this AD merely restates the requirements of paragraph (f)(1) of AD 2007-18-51. As allowed by the phrase, “unless the actions have already been done,” if the applicable initial inspections required by paragraph (f)(1) of AD 2007-18-51 have already been done, this AD does not require that those inspections be repeated until the repetitive interval of 3,000 flight cycles.
Within 10 days after the effective date of this AD: Do a detailed inspection or a borescope inspection of each main slat track downstop assembly to verify proper installation of the slat track hardware (i.e., the bolt, washers, downstops, stop location, and nut shown in Figure 1 of Boeing Service Letter 737-SL-57-084-B, dated July 10, 2007, and in this AD). Proper installation of the sleeve need not be confirmed, and the stop location part may be installed on either the inboard or the outboard side of the slat track. If any part is missing or is installed improperly, before further flight, install a new or serviceable part using a method approved in accordance with the procedures specified in paragraph (h) of this AD; and do a detailed inspection of the inside of the slat can for foreign object debris (FOD) and damage. Before further flight, remove any FOD found and repair any damage found using a method approved in accordance with the procedures specified in paragraph (h) of this AD. Using Boeing Multi Operator Message Number 1-523812011-1, issued August 25, 2007; or 1-527463441-1, issued August 28, 2007; is one approved method for verifying proper installation; installing a new or serviceable part; and inspecting for damage and FOD, and removing FOD and repairing damage. Repeat the actions required by paragraph (f) of this AD thereafter at intervals not to exceed 3,000 flight cycles.
Note 2: Paragraph (g) of this AD merely restates the requirements of paragraph (f)(2) of AD 2007-18-51. As allowed by the phrase, “unless the actions have already been done,” if the torque application required by paragraph (f)(2) of AD 2007-18-51 has already been done, this AD does not require that the torque application be repeated.
Within 24 days after receipt of AD 2007-18-51: Apply a torque between 50 to 80 inch-pounds to the nut. The bolt head must be held with the torque applied to the nut.
Note 3: 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.”
