Airworthiness Directive · Amendment 39-22440 · Wings
Boeing Airplanes
This AD applies to all Boeing Model B-17E, B-17F, and B-17G airplanes, certificated in any category.
The FAA is adopting a new airworthiness directive (AD) for all Boeing Model B-17E, B-17F, and B-17G airplanes. This AD was prompted by a report indicating that the left front spar lower fitting had completely separated at the wing-to-fuselage joint, and the equivalent joint on the right side of the airplane was cracked. This AD requires inspections of the wing terminal-to-spar chord joints, and repair if necessary. The FAA is issuing this AD to address the unsafe condition on these products.
Before further flight: Perform inspections to detect cracking and corrosion by doing the actions specified in either paragraph (g)(1) or (2) of this AD. No action is required by this AD if all wing terminal fittings have been inspected in accordance with paragraph (b)(1) of AD 2001-22-06, Amendment 39-12485 (66 FR 54111, October 26, 2001), and, as of the effective date of this AD, no more than 10 years or 2,500 flight hours have accumulated since that inspection.
(1) Separate all 8 wing terminal-to-spar chord joints (wings off) and perform a magnetic particle inspection of the steel terminal fittings and an eddy current inspection of the 8 inboard holes in the end of the spar chord, in accordance with procedures approved by the Manager, West Certification Branch, FAA.
(2) On the left and right lower forward terminal fitting-to-spar chord joint assemblies, remove the most inboard fastener common to the spar cord and the terminal fitting, and do an eddy current bolt hole inspection on the steel terminal fittings and on the aluminum spar chord in accordance with procedures approved by the Manager, West Certification Branch, FAA.
If any cracking or corrosion is found during the inspections required by paragraph (g) of this AD, repair before further flight using a method approved by the Manager, West Certification Branch, FAA.
At the applicable time specified in paragraph (i)(1) or (2) of this AD, submit a report of all findings (positive and negative) from the inspections required by paragraph (g) of this AD. The report must include a statement that no discrepancies were found or a description of any discrepancies found including the condition of the wing terminal-to-spar chord joints (terminal fitting and spar chord), the inspection procedure used, the airplane serial number, and the number of flight hours on the airplane. Submit the report to Eric Schrieber, Senior Engineer, West Certification Branch Airframe Section, email Eric.Schrieber@faa.gov.
(1) If the inspection was done on or after the effective date of this AD: Submit the report within 10 days after the inspection.
(2) If the inspection was done before the effective date of this AD: Submit the report within 10 days after the effective date 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
