Airworthiness Directive · Amendment 39-14310 · Boeing Model 737-100, -200, and -200C Series Airplanes
Boeing Model 737-100, -200, and -200C Series Airplanes
This AD applies to Boeing Model 737-100, -200, and -200C series airplanes; line numbers 1 through 1585 inclusive; certificated in any category.
The FAA is adopting a new airworthiness directive (AD) for certain Boeing Model 737-100, -200, and -200C series airplanes. This AD requires a one-time detailed inspection for cracking of the lugs of the inboard attach fittings of the wing leading edge slat tracks at slat numbers 2 and 5; prior or concurrent actions for certain airplanes; repetitive high-frequency eddy current (HFEC) inspections for cracking of the lug surfaces of those inboard attach fittings if necessary; and replacement of the attach fittings with new, improved fittings. This AD results from reports of damage to the lugs of certain inboard attach fittings of the leading edge slat tracks. We are issuing this AD to prevent a lifted slat, which, if the airplane performs any non-normal maneuver during takeoff or landing at very high angles of attack, could lead to the loss of the slat and reduced 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.
The term “service bulletin,” as used in this AD, means the Accomplishment Instructions of Boeing Special Attention Service Bulletin 737-57-1273, Revision 2, dated October 30, 2003; unless otherwise specified in this AD.
Prior to the accumulation of 7,000 total flight cycles or within 12 months after the effective date of this AD, whichever occurs later, perform a one-time detailed inspection for cracking and damage of the inboard attach fittings at slats 2 and 5 of the wing leading edge in accordance with the service bulletin.
Note 1: For the purposes of this AD, a detailed inspection is “An intensive visual examination of a specific structural area, system, installation, or assembly to detect damage, failure, or irregularity. Available lighting is normally supplemented with a direct source of good lighting at intensity deemed appropriate by the inspector. Inspection aids such as mirror, magnifying lenses, etc., may be used. Surface cleaning and elaborate access procedures may be required.”
(1) If any crack or damage is found, replace the cracked inboard attach fitting in accordance with paragraph (h) of this AD.
(2) If no crack or damage is found, within 4,500 flight cycles or 18 months after the detailed inspection required by paragraph (g) of this AD, whichever occurs first, perform a high-frequency eddy current (HFEC) inspection for cracking of the lugs of the inboard attach fittings in accordance with the service bulletin. If no crack is found, repeat the HFEC inspection at intervals not to exceed 4,500 flight cycles.
Replace the aluminum inboard attach fittings with new, improved steel fittings at the applicable compliance time in paragraph (h)(1) or (h)(2) of this AD in accordance with the service bulletin. Replacement of any aluminum fitting with a new, improved steel fitting terminates the one-time detailed inspection and the repetitive HFEC inspections required by paragraph (g) of this AD for that fitting.
(1) If any crack or damage is found during any inspection required by paragraphs (g) or (i) of this AD, before further flight.
(2) If no crack or damage is found during any inspection required by paragraph (g) or (i) of this AD, within 30,000 flight cycles or within 120 months after the effective date of this AD, whichever occurs first.
(i) For airplanes listed in Group 2 of the service bulletin: Prior to or during the one-time detailed inspection for cracking or damage required by paragraph (g) of this AD or during replacement of the fitting required by paragraph (h) of this AD, whichever occurs first, perform a detailed inspection on slats 2 and 5 for interference of the slat tab support clips with the slat track attach fittings and trim the support clips to eliminate any interference with the attach fittings as applicable; in accordance with Figure 3 of the Accomplishment Instructions of Boeing Service Bulletin 737-57-1080, Revision 3, dated September 24, 1992; and replace any cracked or damaged aluminum attach fitting with a new, improved steel fitting in accordance with paragraph (h) of this AD.
Actions accomplished before the effective date of this AD in accordance with Boeing Service Bulletin 737-57-1080, dated September 10, 1973; Revision 1, dated February 25, 1983; or Revision 2, dated August 24, 1989; are considered acceptable for compliance with the corresponding actions specified in paragraph (i) of this AD.
