AD 2006-07-10

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 listed in Boeing Service Bulletin 727-53-0153, Revision 5, dated December 14, 1989: Visually inspect the forward entry doorway frame for cracks in accordance with Boeing Service Bulletin 727-53-0153, dated February 1, 1980, or Revisions 1 through 5, at the earlier of the times indicated in subparagraphs (f)(1) or (f)(2) of this AD. Repeat the inspection at intervals not to exceed 3,700 landings until accomplishment of the one-time high frequency eddy current (HFEC) inspection for cracking and the one-time dimensional inspection for anomalies required by paragraph (i) of this AD, or the one-time dimensional inspection for anomalies and the initial HFEC inspection for cracking of the forward frame of the forward entry doorway at BS 303.9 specified in paragraph (h) of this AD, as applicable.

(1) Within the next 1,850 landings after March 11, 1983 (the effective date of AD 83-03-01, amendment 39-4561), or prior to accumulating a total of 25,000 landings, whichever occurs later; or

(2) Within the next 1,850 landings after May 16, 1986 (the effective date of AD 83-03-01 R1, amendment 39-5283), or prior to accumulating a total of 15,000 landings, whichever occurs later.

(g) For airplanes modified in accordance with Boeing Service Bulletin 727-53-0153, dated February 1, 1980; through Revision 4, dated November 8, 1985; conduct the inspections described in paragraph (f) of this AD prior to the accumulation of 10,000 landings after the modification or within the next 3,700 landings after May 28, 1991 (the effective date of AD 91-09-07), whichever occurs later. Repeat the inspection at intervals not to exceed 3,700 landings until accomplishment of the one-time HFEC inspection for cracking and the one-time dimensional inspection for anomalies required by paragraph (i) of this AD, or the one-time dimensional inspection for anomalies and the initial HFEC inspection for cracking of the forward frame of the forward entry doorway at BS 303.9 specified in paragraph (h) of this AD, as applicable.

For Group 1 airplanes as defined by Boeing Alert Service Bulletin (ASB) 727-53A0153, Revision 7, dated August 14, 2003, with the exception of certain Group 1 airplanes specified in paragraph (i) of this AD: Perform a one-time dimensional inspection for anomalies (e.g., minimum dimension requirements, jagged edges, chafing, nicks, or gouges) of the web cutouts at stringers S-15 and S-16, and HFEC inspections for cracking of the forward frame of the forward entry doorway at BS 303.9; in accordance with Figure 1 of the Accomplishment Instructions of Revision 7 of the ASB at the times specified in paragraph (h)(1) or (h)(2) of this AD, as applicable. With the exception of the one-time dimensional inspection (Step 1 of Figure 1) of the web cutouts at S-15L and S-16L, repeat the HFEC inspections for cracking of the forward frame of the forward entry doorway at BS 303.9 at intervals not to exceed 3,700 flight cycles until the requirements of paragraph (l) of this AD have been accomplished.

(1) For Group 1 airplanes that have not been modified or repaired in accordance with any issue of the service bulletin through Revision 7 inclusive specified in Table 1 of this AD: Perform the inspection before the accumulation of 15,000 total flight cycles, or within 1,800 flight cycles after the effective date of this AD, whichever occurs later.

(2) For Group 1 airplanes that have been modified as specified in Boeing Repair Kit 65C20303-1 in accordance with any issue of the service bulletin through Revision 4 inclusive as specified in Table 1 of this AD: Perform the inspection before the accumulation of 10,000 flight cycles after the modification, or within 1,800 flight cycles after the effective date of this AD, whichever occurs later.

(i) For Group 1 airplanes, as defined by Boeing ASB 727-53A0153, Revision 7, dated August 14, 2003, that have been modified in accordance with Revision 5 or 6 of Boeing Service Bulletin 727-53-0153 as specified in Table 1 of this AD, or that have been repaired in accordance with Boeing Repair Kit 65C20303-8 or -25 as specified in Revision 2 through Revision 6 inclusive of the service bulletin as specified in Table 1 of this AD: Within 4,500 flight cycles after the effective date of this AD, do a one-time HFEC for cracking and a dimensional inspection for any anomaly (e.g., minimum dimension requirements, jagged edges, chafing, nicks or gouges) of the web cutouts at stringers S-15L and S-16L of the forward frame of the forward entry doorway at BS 303.9, in accordance with Step 1 and Step 2 of Figure 1 of the Accomplishment Instructions of Boeing ASB 727-53A0153, Revision 7, dated August 14, 2003. For these airplanes, accomplishment of the HFEC, dimensional inspections, and any applicable corrective actions, constitutes terminating action for all the repetitive inspection requirements of this AD.

For Group 2 airplanes, as defined by Boeing ASB 727-53A0153, Revision 7, dated August 14, 2003, that have not been modified or repaired in accordance with Revision 7 of the ASB: Before the accumulation of 17,000 total flight cycles, or within 4,500 flight cycles after the effective date of this AD, whichever occurs later, perform a one-time dimensional inspection for anomalies (e.g., minimum dimension requirements, jagged edges, chafing, nicks, or gouges) of the web cutouts at stringers S-15 and S-16, and HFEC inspections for cracking of the forward frame of the forward entry doorway at BS 303.9; in accordance with Figure 2 of the Accomplishment Instructions of Revision 7 of the ASB. With the exception of the one-time dimensional inspection (Step 1 of Figure 2) of the web cutouts at S-15L and S-16L, repeat the HFEC inspections for cracking of the forward frame of the forward entry doorway at BS 303.9 at intervals not to exceed 3,700 flight cycles until the requirements of paragraph (l) of this AD have been accomplished.

If any cracking is detected during any inspection, or any anomaly is detected during any dimensional inspection required by this AD: Before further flight, accomplish the actions in paragraph (k)(1) or (k)(2) of this AD, as applicable.

(1) For any cracking that is within the limits specified in the Accomplishment Instructions of Boeing ASB 727-53A0153, Revision 7, dated August 14, 2003: Repair the cracking in accordance with Revision 7 of the ASB.

(2) For any cracking that is outside the limits specified in the Accomplishment Instructions of Boeing ASB 727-53A0153, Revision 7, dated August 14, 2003, or for any anomaly that is detected during any dimensional inspection required by this AD: Repair in accordance with a method approved by the Manager, Seattle Aircraft Certification (ACO), FAA; or in accordance with the procedures specified in paragraph (n) of this AD.

For airplanes specified in paragraph (l)(1) or (l)(2) of this AD: At the time specified in paragraph (m) of this AD, perform the inspections specified in Figure 1 or Figure 2, as applicable, of Revision 7 of Boeing ASB 727-53A0153, dated August 14, 2003, and as specified by paragraph (h) or (j) of this AD, as applicable. Before further flight, following the inspections, modify the forward frame in accordance with the Accomplishment Instructions of Revision 7 of the ASB. Concurrent accomplishment of the inspections and modification constitutes terminating action for the repetitive inspections required by this AD.

(1) Group 1 airplanes that have not been modified or repaired in accordance with Boeing Repair Kit 65C20303-8 or -25, as specified in Boeing Service Bulletin 727-53-153, Revision 2, dated December 3, 1982; Revision 3, dated June 17, 1983; or Revision 4, dated November 8, 1985; Boeing Service Bulletin 727-53-0153, Revision 5, dated December 14, 1989; or Revision 6, dated August 27, 1992; or Boeing ASB 727-53A0153, Revision 7, dated August 14, 2003.

(2) Group 2 airplanes that have not been repaired or modified in accordance with Revision 7 of Boeing ASB 727-53A0153, dated August 14, 2003.

Note 1: Accomplishment of the terminating actions specified in paragraph (i) or (l) of this AD does not relieve the operator of responsibility to comply with the inspection requirements of the operator's standard structural maintenance program.

Accomplish the actions required in paragraph (l) of this AD at the later of the times specified in paragraph (m)(1) or (m)(2) of this AD.

(1) Prior to the accumulation of 60,000 total flight cycles.

(2) Within 48 months or 7,200 flight cycles after the effective date of this AD, whichever occurs first.