Airworthiness Directive · Amendment 39-16470 · Wings
BAE SYSTEMS (OPERATIONS) LIMITED Model BAe 146 and Avro 146-RJ Airplanes
This AD applies to all BAE Systems (OPERATIONS) LIMITED Model BAe 146-100A, -200A, and -300A airplanes, and Model Avro 146-RJ70A, 146-RJ85A, and 146-RJ100A airplanes, certificated in any category.
We are adopting a new airworthiness directive (AD) for the products listed above. This AD results from mandatory continuing airworthiness information (MCAI) originated by an aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as:
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 in paragraph (g)(1) or (g)(2) of this AD, do a general visual inspection to identify the type of bolt and nut at each location, in accordance with the Accomplishment Instructions of BAE SYSTEMS (OPERATIONS) LIMITED Inspection Service Bulletin ISB.57-033, Revision 9, dated October 10, 2006.
(1) For airplanes on which neither Modification HCM01447A nor repair information leaflet (RIL) HC536H9156 (at any location) has been done as of the effective date of this AD, the compliance time for the inspection is at the later of the times specified in paragraphs (g)(1)(i) and (g)(1)(ii) of this AD.
(i) Within 12 months after the effective date of this AD, or within 2 years after the last inspection done in accordance with BAE SYSTEMS (OPERATIONS) LIMITED Inspection Service Bulletin ISB.57-033, whichever occurs later, without exceeding 4,000 flight cycles after the last inspection.
(ii) Within 250 flight cycles or 3 months after the effective date of this AD, whichever occurs first.
(2) For airplanes on which either Modification HCM01447A or RIL HC536H9156 (at any location) has been done as of the effective date of this AD, the compliance time for the inspection is at the latest of the times specified in paragraphs (g)(2)(i), (g)(2)(ii), and (g)(2)(iii) of this AD.
(i) Before the accumulation of 4,000 total flight cycles.
(ii) Within 4,000 flight cycles after all bolts are inspected and replaced in accordance with BAE SYSTEMS (OPERATIONS) LIMITED Inspection Service Bulletin ISB.57-033.
(iii) Within 12 months after the effective date of this AD.
(h) At the applicable time in paragraph (g)(1) or (g)(2) of this AD, do detailed inspections of the bolt installation for proper nut installation, nut seating, and fuel seepage; a detailed inspection for gaps between the fitting and wing structure; if Hi-Loks are installed, measure the torque of the nuts to determine the specifications in the torque figures shown in Table 2. of the Accomplishment Instructions of BAE SYSTEMS (OPERATIONS) LIMITED Inspection Service Bulletin ISB.57-033, Revision 9, dated October 10, 2006; and either an ultrasonic inspection for damaged bolts or a torque measurement of the tension bolts to determine the specifications in the torque figures shown in Table 3 of the Accomplishment Instructions of BAE SYSTEMS (OPERATIONS) LIMITED Inspection Service Bulletin ISB.57-033, Revision 9, dated October 10, 2006. Do all actions in accordance with the Accomplishment Instructions of BAE SYSTEMS (OPERATIONS) LIMITED Inspection Service Bulletin ISB.57-033, Revision 9, dated October 10, 2006.
(i) If, during any inspection required by paragraph (h) of this AD, any defect (e.g., evidence of fuel seepage, damaged bolts or low bolt torque, loose or rotating nuts, suspect integrity of the bolt/nut assembly, or gaps between the fitting and wing structure) is found, before further flight, do the actions specified in paragraphs (i)(1), (i)(2), (i)(3), (i)(4), and (i)(5) of this AD, in accordance with the Accomplishment Instructions of BAE SYSTEMS (OPERATIONS) LIMITED Inspection Service Bulletin ISB.57-033, Revision 9, dated October 10, 2006.
(1) Do a detailed inspection of the sealant for cracks at and around all rear spar root joint attachment bolts.
(2) Do a detailed inspection of the bolt for damage or evidence of the nut being tightened to the end of the thread.
(3) Do a detailed inspection of the wear pattern on the seating surfaces of the bolt and nut to determine if the bolt and nut have been evenly seated on the structure.
(4) Do a detailed inspection of the bolt hole and surrounding area for damage.
(5) Do a detailed inspection to determine that the hole edge radius on the forward face of the rear spar meets the dimensions specified in Table 4 of the Accomplishment Instructions of BAE SYSTEMS (OPERATIONS) LIMITED Inspection Service Bulletin ISB.57-033, Revision 9, dated October 10, 2006.
(j) If during any inspection required by paragraph (h) or (i) of this AD, any defects (e.g., evidence of fuel seepage, damaged bolts or low bolt torque, loose or rotating nuts, suspect integrity of the bolt/nut assembly, gaps between the fitting and wing structure, cracked sealant, bolt damage or evidence of the nut being tightened to the end of the thread, uneven seating of the bolt and nut, bolt hole and surrounding area damage, or hole edge radius out of dimensions specified in Table 4 of the Accomplishment Instructions of BAE SYSTEMS (OPERATIONS) LIMITED Inspection Service Bulletin ISB.57-033, Revision 9, dated October 10, 2006), is found, before further flight, do all applicable correction actions, which include either replacing the bolt or repairing the defect, in accordance with the Accomplishment Instructions of BAE SYSTEMS (OPERATIONS) LIMITED Inspection Service Bulletin ISB.57-033, Revision 9, dated October 10, 2006.
(k) Repeat the inspections in paragraph (h) of this AD thereafter, at the applicable time specified in Table 1 of this AD, for each individual location.
| If the location has— | Then repeat the inspection— |
|---|---|
| A Hi-Lok bolt | Within 4,000 flight cycles or 24 months, whichever occurs earlier, after doing the last inspection. |
| A tension bolt that was not replaced during the inspections in paragraphs (h) and (i) of this AD and no defects were found | Within 8,000 flight cycles or 48 months, whichever occurs earlier, after doing the last inspection. |
| A tension bolt that was replaced as required by paragraph (j) of this AD | Within 4,000 flight cycles or 24 months, whichever occurs earlier after doing the replacement. |
| A tension bolt that was not replaced and any defects were repaired as required by paragraph (j) of this AD | Within 4,000 flight cycles or 24 months, whichever occurs earlier after doing the repair specified in paragraph (j) of this AD. |
Note 1: This AD differs from the MCAI and/or service information as follows: Although BAE SYSTEMS (OPERATIONS) LIMITED Service Bulletin ISB.57-033, Revision 9, dated October 10, 2006, allows additional time to rectify the defect for the corrective action depending on the condition, this AD requires rectifying the defect before further flight.
