Airworthiness Directive · Amendment 39-15641 · Boeing Model 737-100, -200, -200C, -300, -400, and -500 Series Airplanes
Boeing Model 737-100, -200, -200C, -300, -400, and -500 Series Airplanes
Superseded. A later AD replaced this one: AD 2014-23-10. Comply with the one in force.
This AD applies to the airplanes, certificated in any category, identified in Table 1 of this AD.
| Boeing model— | As identified in Boeing Alert Service Bulletin— |
|---|---|
| 737-100, -200, and -200C series airplanes | 737-53A1197, dated August 25, 2006. |
| 737-300, -400, and -500 series airplanes | 737-53A1188, Revision 2, dated May 9, 2007, or 737-53A1197, dated August 25, 2006. |
We are adopting a new airworthiness directive (AD) for certain Boeing Model 737-100, -200, -200C, -300, -400, and -500 series airplanes. This AD requires repetitive inspections to detect cracking of the body station 303.9 frame, and corrective action if necessary. This AD also provides for optional terminating action for the repetitive inspections. This AD results from reports of cracks found at the cutout in the web of body station frame 303.9 inboard of stringer 16L. We are issuing this AD to detect and correct such cracking, which could prevent the left forward entry door from sealing correctly, and could cause in-flight decompression 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 identified in Boeing Alert Service Bulletin 737-53A1188, Revision 2, dated May 9, 2007, including airplanes modified by the repair/preventive change specified in the original version, dated April 9, 1998; or Revision 1, dated March 18, 1999; of the service bulletin: Do detailed and high frequency eddy current (HFEC) inspections in the web and doubler around the slotted holes in the frame web at stringers 15L and 16L, in accordance with the Accomplishment Instructions of Revision 2 of the service bulletin. Do the inspections at the applicable time specified in paragraph 1.E. of Revision 2 of the service bulletin, except as provided by paragraph (h) of this AD. Do all applicable corrective actions before further flight in accordance with Revision 2 of the service bulletin, except as provided by paragraph (i) of this AD. Repeat the inspections at intervals not to exceed 4,500 flight cycles until accomplishment of the repair/preventive change in accordance with Revision 2 of the service bulletin, which terminates the repetitive inspection requirements. A repair/preventive change done in accordance with the original version or Revision 1 of the service bulletin does not terminate the repetitive inspections, but the repetitive inspections may be terminated after the existing kit is replaced with a new kit in accordance with paragraph 3.B., Part II, step 3, or Part III, step 3, of Revision 2 of the service bulletin.
For airplanes identified in Boeing Alert Service Bulletin 737-53A1197, dated August 25, 2006: Do an ultrasound inspection of the slot-shaped cutout in the web for the door stop strap at stringer 16L, an HFEC inspection of the web along the upper and lower edges of the doubler around the doorstop strap at stringer 16L, and a detailed inspection of the web around the doubler for the cutout at stringer 16L, in accordance with the Accomplishment Instructions of the service bulletin. Do the inspections at the applicable time specified in paragraph 1.E. of the service bulletin, except as provided by paragraph (h) of this AD. Do all applicable corrective actions before further flight in accordance with the service bulletin, except as provided by paragraph (i) of this AD. Repeat the inspections at intervals not to exceed 4,500 flight cycles, until accomplishment of the repair/preventive change in accordance with the service bulletin, which terminates the repetitive inspections.
Where Boeing Alert Service Bulletin 737-53A1188, Revision 2, dated May 9, 2007, and Boeing Alert Service Bulletin 737-53A1197, dated August 25, 2006, specify a compliance time after release of the service bulletin, this AD requires compliance within the specified time after the effective date of this AD. For the initial inspection, the grace period for airplanes that have exceeded the specified threshold is extended to 4,500 flight cycles after the effective date of this AD.
(i) Where Boeing Alert Service Bulletin 737-53A1188, Revision 2, dated May 9, 2007, and Boeing Alert Service Bulletin 737-53A1197, dated August 25, 2006, specify to contact Boeing for appropriate action, including repair of damage outside the scope of the service bulletin, repair using a method approved in accordance with the procedures specified in paragraph (j) of this AD.
