85-19-08 BRITISH AEROSPACE: Amendment 39-5313. Applies to Model 3101 (includes Model 3100) airplanes (serial numbers 601 through 666) certificated in any category.
Compliance: Required within seven days after receipt of this AD unless already accomplished.
To prevent the possibility of wing droop development and structural damage to the forward wing spar fuselage attachment and resulting loss of control of the airplane, accomplish the following:
(a) Remove wing-to-fuselage fairing panels numbers F19 and F20.
(b) Using as a reference BAe Model 3100 Illustrated Parts Catalog, Chapter 57-00- 00 Figure 3 wing installation and using a suitable light source, visually inspect and repair as required item number 210 spigot (pin) Part No. 13781B7 (LH and RH), in accordance with the following criteria:
(i) If no gap exists between the spigot flange and the fuselage post, and if the locking bolt, washer and nut (items 205, 200 and 195 respectively) securing the spigotare in position and secure, install panel numbers F19 and F20 and return the airplane to service.
(ii) If little or no gap exists between the spigot flange and the fuselage post, and if the locking bolt, washer and nut are not secure, prior to further flight accomplish the following:
(A) Remove the loading from the wing to the fuselage joint and push the spigot (pin) into the spigot housing, and
(B) Install the locking bolt (Part No. A102-18D) with the head forward, the nut (Part No. A126 D66) and the washer (Part No. SP124D). Replace panels F19 and F20 and return the airplane to service.
(C) If the locking bolt (Part No. A102-18D) cannot be installed without rotation of the spigot, prior to further flight accomplish the repair procedures described in paragraph (c) of this AD.
(iii) If a large gap exists between the spigot flange and the fuselage post which results in loss of engagement with the spigot housing plate (item 215 LH and 220 RH), prior to further flight accomplish the repair procedures described in paragraph (c) of this AD.
(iv) If other structural deformation or damage is observed relating to improper spigot installation, prior to further flight obtain and accomplish the repair procedures in accordance with paragraph (c) of this AD.
(v) If the fuselage vertical post outboard bushing is found to be displaced, prior to further flight repair in accordance with the instructions in Figure 1 of British Aerospace Service Bulletin No. 57-A-JA 840917 dated January 25, 1985.
(c) Alternate methods of compliance and repair procedure may be used if approved by either the Manager of the FAA Brussels Aircraft Certification Office, FAA, AEU-100, c/o American Embassy, 1000 Brussels, Belgium, or the Manager of the Small Aircraft Certification Division, FAA, Central Region, ACE-100, 601 East 12th Street, Kansas City, Missouri 64106.
(d) Report, in writing, all defects found to the Manager, Small Aircraft Certification Division, FAA, Central Region, within 48 hours of the inspection. (Reporting approved by the Office of Management and Budget under OMB No. 2120-0056.)
This amendment becomes effective May 26, 1986, as to all persons except those persons to whom it was made immediately effective by priority letter AD 85-19-08, issued September 26, 1985, which contained this amendment.