Airworthiness Directive · Amendment 39-18027 · Fuselage
The Boeing Company Airplanes
This AD applies to The Boeing Company Model 747-400F series airplanes, certificated in any category, as identified in Boeing Service Bulletin 747-53A2443, Revision 2, dated August 2, 2013.
We are superseding Airworthiness Directive (AD) 2005-13-05, which applied to certain Boeing Model 747-400F series airplanes. AD 2005-13-05 required inspections for cracking of the web, upper chord, and upper chord strap of the upper deck floor beams, and repair of any cracking. AD 2005-13-05 also required a preventive modification of the upper deck floor beams, and repetitive inspections for cracking after accomplishing the modification. This new AD retains these actions and requires a second modification, repetitive inspections for cracking, and repair if necessary. This AD was prompted by a determination that the upper chords of the upper deck floor beams at certain stations are structures that are susceptible to widespread fatigue damage, and that certain airplanes with an initial modification require a second modification for the airplane to meet its limit of validity (LOV). We are issuing this AD to detect and correct fatigue cracking in certain upper chords of the upper deck floor beam, which could result in reduced structural integrity of the airplane and rapid decompression or reduced controllability of the airplane.
This paragraph restates the requirements of paragraph (g) of AD 2005-13-05, Amendment 39-14141 (70 FR 35989, June 22, 2005), with revised service information. Before the accumulation of 15,000 total flight cycles, or within 1,000 flight cycles after July 27, 2005 (the effective date of AD 2005-13-05), whichever is later: Accomplish detailed and open-hole high frequency eddy current (HFEC) inspections for cracking of the web, upper chord, and upper chord strap of the upper deck floor beams, by doing all the applicable actions in accordance with Part 3.B.1. of the Accomplishment Instructions of Boeing Service Bulletin 747-53A2443, dated May 9, 2002; or Part 1 of the Accomplishment Instructions of Boeing Service Bulletin 747-53A2443, Revision 2, dated August 2, 2013. As of the effective date of this AD, only Boeing Service Bulletin 747-53A2443, Revision 2, dated August 2, 2013, may be used.
This paragraph restates the requirements of paragraph (h) of AD 2005-13-05, Amendment 39-14141 (70 FR 35989, June 22, 2005), with revised service information and revised repair approval language. If any crack is found during any inspection required by paragraph (g) of this AD: Before further flight, accomplish the actions required by paragraph (h)(1) and (h)(2) of this AD.
(1) Repair in accordance with the Accomplishment Instructions of Boeing Service Bulletin 747-53A2443, dated May 9, 2002; or the Accomplishment Instructions of Boeing Service Bulletin 747-53A2443, Revision 2, dated August 2, 2013; except where these service bulletins specify to contact Boeing for appropriate action, before further flight, repair the cracking using a method approved in accordance with the procedures specified in paragraph (o) of this AD. As of the effective date of this AD, only Boeing Service Bulletin 747-53A2443, Revision 2, dated August 2, 2013, may be used.
(2) Accomplish the inspections and preventive modification of the floor beams by doing all the actions in accordance with Part 3.B.2. or Part 3.B.3., as applicable, of the Accomplishment Instructions of Boeing Service Bulletin 747-53A2443, dated May 9, 2002; or Part 2 or Part 3, as applicable, of the Accomplishment Instructions of Boeing Service Bulletin 747-53A2443, Revision 2, dated August 2, 2013. If any crack is found during any inspection, before further flight, repair as required by paragraph (h)(1) of this AD. As of the effective date of this AD, only Boeing Service Bulletin 747-53A2443, Revision 2, dated August 2, 2013, may be used.
This paragraph restates the requirements of paragraph (i) of AD 2005-13-05, Amendment 39-14141 (70 FR 35989, June 22, 2005), with revised service information. If no crack is found during any inspection required by paragraph (g) of this AD: Accomplish the actions required by either paragraph (i)(1) or (i)(2) of this AD, at the time specified.
(1) Before further flight: Accomplish the inspections and preventive modification of the floor beam by doing all the actions in accordance with Part 3.B.2 or Part 3.B.3., as applicable, of the Accomplishment Instructions of Boeing Service Bulletin 747-53A2443, dated May 9, 2002; or Part 2 or Part 3, as applicable, of the Accomplishment Instructions of Boeing Service Bulletin 747-53A2443, Revision 2, dated August 2, 2013. If the preventive modification is performed concurrently with the inspections required by paragraph (g) of this AD, the upper chord straps must be removed when performing the open-hole HFEC inspection. If any crack is found during any inspection, before further flight, repair as required by paragraph (h)(1) of this AD. As of the effective date of this AD, only Boeing Service Bulletin 747-53A2443, Revision 2, dated August 2, 2013, may be used.
(2) Before the accumulation of 20,000 total flight cycles, or within 1,000 flight cycles after July 27, 2005 (the effective date of AD 2005-13-05, Amendment 39-14141 (70 FR 35989, June 22, 2005), whichever is later: Accomplish the inspections and preventive modification of the upper deck floor beams, by doing all the actions in accordance with Part 3.B.2. or 3.B.3. as applicable, of the Accomplishment Instructions of Boeing Service Bulletin 747-53A2443, dated May 9, 2002; or Part 2 or Part 3, as applicable, of the Accomplishment Instructions of Boeing Service Bulletin 747-53A2443, Revision 2, dated August 2, 2013. If any crack is found during any inspection, before further flight, repair as required by paragraph (h)(1) of this AD. As of the effective date of this AD, only Boeing Service Bulletin 747-53A2443, Revision 2, dated August 2, 2013, may be used.
This paragraph restates the requirements of paragraph (j) of AD 2005-13-05, Amendment 39-14141 (70 FR 35989, June 22, 2005), with revised service information. Within 15,000 flight cycles after accomplishing the applicable preventive modification required by paragraph (h)(2), (i)(1), or (i)(2) of this AD: Accomplish the applicable inspections required by either paragraph (j)(1) or (j)(2) of this AD; if any crack is found during any inspection, before further flight, repair as required by paragraph (h)(1) of this AD. As of the effective date of this AD, for airplanes on which the alternative preventive modification, as identified in the NOTE after step 3. of “PART 2—INSPECTION AND PREVENTIVE MODIFICATION,” or as identified in the NOTE after step 4. of “PART 3—INSPECTION AND PREVENTIVE MODIFICATION,” of the Accomplishment Instructions of Boeing Service Bulletin 747-53A2443, Revision 2, dated August 2, 2013, has been done, only the inspection specified by paragraph (j)(1) of this AD may be used.
(1) Accomplish detailed and surface HFEC inspections for cracking of the web, upper chord, and upper chord strap of the upper deck floor beams, by doing all the applicable actions in accordance with Part 3.B.4. of the Accomplishment Instructions of Boeing Service Bulletin 747-53A2443, dated May 9, 2002; or Part 4 of the Accomplishment Instructions of Boeing Service Bulletin 747-53A2443, Revision 2, dated August 2, 2013. If no crack is found, repeat the inspections at intervals not to exceed 1,000 flight cycles. As of the effective date of this AD, only Boeing Service Bulletin 747-53A2443, Revision 2, dated August 2, 2013, may be used.
(2) Accomplish detailed and open-hole HFEC inspections for cracking of the web, upper chord, and strap of the upper deck floor beams, by doing all the applicable actions in accordance with Part 3.B.5. of the Accomplishment Instructions of Boeing Service Bulletin 747-53A2443, dated May 9, 2002; or Part 5 of the Accomplishment Instructions of Boeing Service Bulletin 747-53A2443, Revision 2, dated August 2, 2013. If no crack is found, repeat the inspections at intervals not to exceed 5,000 flight cycles. As of the effective date of this AD, only Boeing Service Bulletin 747-53A2443, Revision 2, dated August 2, 2013, may be used.
Within 20,000 flight cycles after accomplishing the preventive modification of the Station 340 to Station 520 upper deck floor beams specified in paragraph (h)(2), (i)(1), or (i)(2) of this AD, or within 1,000 flight cycles after the effective date of this AD, whichever occurs later: Accomplish the floor beam hole zero-timing, in accordance with Part 6 of the Accomplishment Instructions of Boeing Service Bulletin 747-53A2443, Revision 2, dated August 2, 2013.
Within 15,000 flight cycles after accomplishing the floor beam hole zero-timing required by paragraph (k) of this AD: Accomplish the applicable inspections required by paragraph (l)(1) or (l)(2) of this AD; if any cracking is found during any inspection, before further flight, repair as required by paragraph (h)(1) of this AD. As of the effective date of this AD, for airplanes on which the alternative preventive modification, as identified in the NOTE after step 3. of “PART 2—INSPECTION AND PREVENTIVE MODIFICATION,” or as identified in the NOTE after step 4. of “PART 3—INSPECTION AND PREVENTIVE MODIFICATION,” of the Accomplishment Instructions of Boeing Service Bulletin 747-53A2443, Revision 2, dated August 2, 2013, has been done, only the inspection method specified by paragraph (l)(1) of this AD may be used.
(1) Accomplish detailed and surface HFEC inspections for cracking of the web, upper chord, and straps of the Station 340 to Station 520 upper deck floor beams, by doing all the applicable actions, in accordance with Part 4 of the Accomplishment Instructions of Boeing Service Bulletin 747-53A2443, Revision 2, dated August 2, 2013. If no cracking is found, repeat the inspections at intervals not to exceed 1,000 flight cycles.
(2) Accomplish detailed and open-hole HFEC inspections for cracking of the web, upper chord, and straps of the Station 340 to Station 520 upper deck floor beams, by doing all the applicable actions, in accordance with Part 5 of the Accomplishment Instructions of Boeing Service Bulletin 747-53A2443, Revision 2, dated August 2, 2013. If no cracking is found, repeat the inspections at intervals not to exceed 5,000 flight cycles.
Where Boeing Service Bulletin 747-53A2443, Revision 2, dated August 2, 2013, specifies a compliance time “after the revision date on this service bulletin,” this AD requires compliance within the specified compliance time after the effective date of this AD.
