Airworthiness Directive · Amendment 39-14506 · Boeing Model 747-200C, -200F, -400, -400D, and -400F Series Airplanes
Boeing Model 747-200C, -200F, -400, -400D, and -400F Series Airplanes
Superseded. A later AD replaced this one: AD 2010-26-10. Comply with the one in force.
This AD applies to Boeing Model 747-200C, -200F, -400, -400D, and -400F series airplanes, certificated in any category; as identified in Boeing Alert Service Bulletin 747-53A2499, dated August 11, 2005.
The FAA is adopting a new airworthiness directive (AD) for certain Boeing Model 747-200C, -200F, -400, -400D, and -400F series airplanes. This AD requires repetitive inspections for cracks in the overlapping (upper) skin, upper fastener row of the lap joints of the fuselage skin in sections 41, 42, and 46; and related investigative and corrective actions, if necessary. This AD results from fatigue tests and an analysis that identified areas of the fuselage lap joints where fatigue cracks can occur. We are issuing this AD to detect and correct fatigue cracks in the overlapping (upper) skin, upper fastener row of the lap joints of the fuselage skin in sections 41, 42, and 46, which could adversely affect the structural integrity 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.
At the applicable time specified in Table 1 of this AD: Do an external surface high frequency eddy current (HFEC), external low frequency eddy current (LFEC), and internal LFEC inspection, as applicable, for cracks in the overlapping (upper) skin, upper fastener row of the lap joints of the fuselage skin in sections 41, 42, and 46, and any applicable related investigative and corrective actions by doing all of the actions in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 747-53A2499, dated August 11, 2005, except as provided by paragraph (h) of this AD. Do any applicable related investigative and corrective actions before further flight.
| For airplanes on which Structural Significant Items (SSIs) F-25G, F-25H, and F-25I— | Inspect— |
|---|---|
| (1) Have not been inspected in accordance with paragraph (d) of AD 2004-07-22, amendment 39-13566 (69 FR 24063, May 3, 2004), using the HFEC method | Before the accumulation of 22,000 total flight cycles, or within 1,000 flight cycles after the effective date of this AD, whichever occurs later. |
| (2) Have been inspected in accordance with paragraph (d) of AD 2004-07-22, using the HFEC method | Within 3,000 flight cycles after the most recent supplemental structural inspection document (SSID) inspection of each applicable structural significant item (as given in Boeing Document D6-35022, “SSID for Model 747 Airplanes,” Revision G, dated December 2000), or within 1,000 flight cycles after the effective date of this AD, whichever occurs later. |
Repeat the applicable inspections required by paragraph (f) of this AD thereafter at intervals not to exceed those specified in paragraph 1.E., “Compliance” (including the note) of Boeing Alert Service Bulletin 747-53A2499, dated August 11, 2005.
Where the service bulletin specifies to contact Boeing for appropriate action, before further flight, repair the crack using a method approved in accordance with the procedures specified in paragraph (i) of this AD.
