Airworthiness Directive · Amendment 39-19092 · Wings
The Boeing Company Airplanes
(1) This AD applies to all The Boeing Company Model 757-200, -200PF, and -200CB series airplanes, certificated in any category.
(2) Installation of Supplemental Type Certificate (STC) ST01518SE [ http://rgl.faa.gov/Regulatory_and_Guidance_Library/rgSTC.nsf/0/38b606833bbd98b386257faa00602538/$FILE/ST01518SE.pdf ] does not affect the ability to accomplish the actions required by this AD. Therefore, for airplanes on which STC ST01518SE is installed, a “change in product” alternative method of compliance (AMOC) approval request is not necessary to comply with the requirements of 14 CFR 39.17.
We are adopting a new airworthiness directive (AD) for all The Boeing Company Model 757-200, -200PF, and -200CB series airplanes. This AD was prompted by reports of slats disbonding on airplanes on which the terminating actions of AD 2005-07-08 had been performed. We have also received reports of slats disbonding on airplanes outside of the applicability of AD 90-23-06, AD 91-22-51, and AD 2005-07-08, which also addressed slat disbonding. This AD requires determining the type of trailing edge slat wedges of the leading edge slats, repetitive inspections for disbonding on certain trailing edge slat wedges, and corrective actions if necessary. This AD also provides an optional terminating action for the repetitive inspections. We are issuing this AD to address the unsafe condition on these products.
At the applicable time specified in paragraph 1.E., “Compliance,” of Boeing Special Attention Service Bulletin 757-57-0066, Revision 1, dated June 7, 2016 (“Boeing SASB 757-57-0066 R1”), except as specified in paragraph (j)(1) of this AD: Inspect each trailing edge slat wedge of the leading edge slats in accordance with Appendixes A, B, C, and D of Boeing SASB 757-57-0066 R1, as applicable, or review the airplane maintenance records, to determine whether the slat wedge is a type A or a type B. If a maintenance records review cannot conclusively determine a slat wedge is a type B, it must be assumed to be a type A slat wedge, or a physical inspection must be done as specified in this paragraph. If a physical inspection cannot determine if a slat wedge is a type A or type B slat wedge, it must be assumed to be a type A slat wedge, or approval of an alternative method of compliance (AMOC) may be requested in accordance with the procedures specified in paragraph (n) of this AD.
For each type A trailing edge slat wedge found during the inspection or records review required by paragraph (g) of this AD: At the applicable time specified in paragraph 1.E., “Compliance,” of Boeing SASB 757-57-0066 R1, except as specified in paragraph (j)(1) of this AD, do an ultrasonic low frequency bond test inspection, a tap test inspection, or a through transmission ultrasonic (TTU) inspection for skin-to-core disbonds of the honeycomb area of the trailing edge slat wedge; do a detailed inspection for aft edge disbonds of the aft edge of the trailing edge slat wedge; do a general visual inspection for any previously accomplished repair; and do all applicable related investigative and corrective actions; in accordance with the Accomplishment Instructions of Boeing SASB 757-57-0066 R1, except as specified in paragraphs (i) and (j)(2) of this AD. Do all applicable related investigative and corrective actions at the applicable time specified in paragraph 1.E., “Compliance,” of Boeing SASB 757-57-0066 R1. Repeat the applicable inspections on each type A trailing edge slat wedge thereafter at the applicable intervals specified in paragraph 1.E., “Compliance,” of Boeing SASB 757-57-0066 R1.
(1) For each type A trailing edge slat wedge with any class 1 disbond repair or any previously accomplished repair subject to the Part 2 inspection as identified in Boeing SASB 757-57-0066 R1: At the applicable time specified in paragraph 1.E., “Compliance,” of Boeing SASB 757-57-0066 R1, do an ultrasonic low frequency bond test inspection, a tap test inspection, or a TTU inspection for skin-to-core disbonds in the repaired area of the trailing edge slat wedge; and do all applicable related investigative and corrective actions; in accordance with the Accomplishment Instructions of Boeing SASB 757-57-0066 R1, except as specified in paragraph (j)(2) of this AD. Do all applicable related investigative and corrective actions before further flight. Repeat the applicable inspection on each type A trailing edge slat wedge thereafter at the applicable interval specified in paragraph 1.E., “Compliance,” of Boeing SASB 757-57-0066 R1.
(2) For each type A trailing edge slat wedge with any time-limited class 2 disbond repair as identified in Boeing SASB 757-57-0066 R1: At the applicable time specified in paragraph 1.E., “Compliance,” of Boeing SASB 757-57-0066 R1, do a detailed inspection for any peeling or deterioration of the aluminum foil tape of the repaired area on the trailing edge slat wedge; and do all applicable related investigative and corrective actions; in accordance with the Accomplishment Instructions of Boeing SASB 757-57-0066 R1, except as specified in paragraph (j)(2) of this AD. Do all applicable related investigative and corrective actions before further flight. Repeat the applicable inspection on each type A trailing edge slat wedge thereafter at the applicable interval specified in paragraph 1.E., “Compliance,” of Boeing SASB 757-57-0066 R1, until a permanent repair is done to complete the actions required for the time-limited class 2 disbond repair, specified as corrective actions in paragraph (h) of this AD.
(3) For each type A trailing edge slat wedge with any permanent class 2 disbond repair as identified in Boeing SASB 757-57-0066 R1: At the applicable time specified in paragraph 1.E., “Compliance,” of Boeing SASB 757-57-0066 R1, do an ultrasonic low frequency bond test inspection or a TTU inspection for any disbonding of the aft edge repaired areas; a detailed inspection for disbonds along the aft edge of the repaired areas; and do all applicable related investigative and corrective actions; in accordance with the Accomplishment Instructions of Boeing SASB 757-57-0066 R1, except as specified in paragraph (j)(2) of this AD. Do all applicable related investigative and corrective actions before further flight. Repeat the applicable inspection on each type A trailing edge slat wedge thereafter at the applicable interval specified in paragraph 1.E., “Compliance,” of Boeing SASB 757-57-0066 R1.
(4) For each type A trailing edge slat wedge with any class 3 or class 4 disbond repair, or any previously accomplished repair subject to Part 5 inspection as identified in Boeing SASB 757-57-0066 R1: At the applicable time specified in paragraph 1.E., “Compliance,” of Boeing SASB 757-57-0066 R1, do the applicable actions specified in paragraphs (i)(4)(i) and (i)(4)(ii) of this AD.
(i) For any class 3 disbond repair with a repair doubler common to the aft edge of the trailing edge slat wedge; for any previously accomplished repair with a repair doubler common to the aft edge of the trailing edge slat wedge; and for any class 4 disbond repair: Do an ultrasonic low frequency bond test inspection or a TTU inspection for any disbonding of the aft edge repaired areas; a detailed inspection for disbonds along the aft edge of the repaired areas; and do all applicable related investigative and corrective actions; in accordance with the Accomplishment Instructions of Boeing SASB 757-57-0066 R1, except as specified in paragraph (j)(2) of this AD. Do all applicable related investigative and corrective actions before further flight. Repeat the applicable inspection on each type A trailing edge slat wedge thereafter at the applicable interval specified in paragraph 1.E., “Compliance,” of Boeing SASB 757-57-0066 R1.
(ii) For any class 3 disbond repair without a repair doubler common to the aft edge of the trailing edge slat wedge; and for any previously accomplished repair without a repair doubler common to the aft edge of the trailing edge slat wedge: Do an ultrasonic low frequency bond test inspection, a tap test inspection, or a TTU inspection for skin-to-core disbonds of the honeycomb area of the trailing edge slat wedge in the repaired area; and do all applicable related investigative and corrective actions; in accordance with the Accomplishment Instructions of Boeing SASB 757-57-0066 R1, except as specified in paragraph (j)(2) of this AD. Do all applicable related investigative and corrective actions before further flight. Repeat the applicable inspection on each type A trailing edge slat wedge thereafter at the applicable interval specified in paragraph 1.E., “Compliance,” of Boeing SASB 757-57-0066 R1.
(1) Where paragraph 1.E., “Compliance,” of Boeing SASB 757-57-0066 R1, specifies a compliance time “after the Revision 1 date of this service bulletin,” this AD requires compliance within the specified compliance time after the effective date of this AD.
(2) If any disbonding is found during any inspection required by this AD, and Boeing SASB 757-57-0066 R1, specifies to contact Boeing for appropriate action: Before further flight, repair the disbonding using a method approved in accordance with the procedures specified in paragraph (n) of this AD.
Replacing a type A trailing edge slat wedge with a type B trailing edge slat wedge terminates the repetitive inspections required by this AD for that wedge if the replacement is done in accordance with the Accomplishment Instructions of Boeing SASB 757-57-0066 R1; or Boeing Alert Service Bulletin 757-57A0063, dated June 26, 2003; or by determining, in accordance with the Accomplishment Instructions of Boeing SASB 757-57-0066, Rl, Appendixes A, B, C, and D (as applicable), that the current wedge installed on the slat is a type B.
(1) Accomplishing the initial inspections required by paragraphs (g) and (h) of this AD on a trailing edge slat wedge terminates all of the requirements of AD 90-23-06, AD 91-22-51, and AD 2005-07-08 for that slat wedge.
(2) Accomplishing the initial inspections required by paragraphs (g) and (h) of this AD on all trailing edge slat wedges terminates all of the requirements of AD 90-23-06, AD 91-22-51, and AD 2005-07-08.
As of the effective date of this AD: A replacement type A wedge may be installed provided that the initial and repetitive inspections and all applicable related investigative and corrective actions specified in paragraphs (h) and (i) of this AD are done within the applicable compliance times specified in paragraphs (h) and (i) of this AD.
The aircraft, engines and makers this AD names, by the model designations in its text. A model listed here may still be outside the AD's serial ranges.
Aircraft
