CTHIn ForceLegislation
AD/B727/182 Amdt 1 - Wing Rear Spar Upper Chord
Boeing 727 Series AeroplanesBoeing 727 Series Aeroplanes
Start here
Get a plain-English read of Boeing 727 Series Aeroplanes
Turn the raw legal text into a practical explanation grounded in AD/B727/182 Amdt 1 - Wing Rear Spar Upper Chord.
Boeing 727 Series Aeroplanes
| AD/B727/182 Amdt 1 | Wing Rear Spar Upper Chord | 6/2005 |
|---|
| Applicability: | Model 727, 727C, 727-100, -100C, -200, and -200F series aircraft, line numbers 1 through 1832. |
|---|---|
| Requirement: | Action in accordance with the technical requirements of FAA AD 2005-05-19 Amdt 39-14008.Note: Boeing Service Bulletin 727-57A0145 Revision 2, or later FAA approved revision refers. |
| Compliance: | As specified in the Requirement document, with a revised effective date of 9 June 2005. |
| This Amendment becomes effective on 9 June 2005. | |
| Background: | The FAA received reports of spanwise stress corrosion cracking of the upper chord of the rear spar of the wing between Wing Butt Line (WBL) 70.5 and the wing tip. One of the cracks was almost long enough to jeopardise the residual strength capability of the upper chord of the rear spar. Such cracking could result in structural failure of the wing and fuel leaks in the aircraft.Amendment 1 is issued in response to a new FAA AD, which requires new repetitive inspections to detect cracks, corrosion, minor surface defects, and existing stop-drilled repairs of cracks in the upper and lower chords of the front and rear spars of the wing. The new AD also requires repairs be carried out if necessary. |
Image unavailable in extracted text
David Villiers
Delegate of the Civil Aviation Safety Authority
27 April 2005