Airworthiness Directive · Amendment 39-17766 · Bell Helicopter Textron Canada (Bell) Helicopters
Bell Helicopter Textron Canada (Bell) Helicopters
Superseded. A later AD replaced this one: AD 2022-23-02. Comply with the one in force.
This AD applies to Model 407 helicopters, serial numbers 53000 through 53475, with tailboom, part number (P/N) 407-030-801-101, -105, or -107, or 407-530-014-101 or -103, installed, certificated in any category.
We are superseding Airworthiness Directive (AD) 2003-05-03 for Bell Model 407 helicopters. AD 2003-05-03 required preflight checking and repetitively inspecting for a crack in certain tailbooms that have been redesigned, replacing the tailboom if there is a crack, modifying and re-identifying certain tailbooms, installing an improved horizontal stabilizer assembly, and assigning a 5,000 hour time-in-service (TIS) limit. This new AD retains the requirements of AD 2003-05-03 and requires additional inspection requirements. This AD was prompted by additional reports of cracked tailboom skins. The actions in this AD are intended to prevent separation of the tailboom and subsequent loss of control of the helicopter.
You are responsible for performing each action required by this AD within the specified compliance time unless it has already been accomplished prior to that time.
(1) For tailboom, P/Ns 407-030-801-101 and -105:
(i) Unmodified per Bell Alert Service Bulletin (ASB) 407-01-48, Revision C, dated August 27, 2007 (ASB 407-01-48):
(A) Before the first flight of each day, visually check the tailboom for a crack, as depicted in Figure 1 to Paragraph (f)(1)(i)(A) of this AD.
(B) For a tailboom with 600 or more hours time-in-service (TIS), within 25 hours TIS and thereafter at intervals not to exceed 50 hours TIS, visually inspect the tailboom for a crack using a 10X or higher magnifying glass by following the Accomplishment Instructions, Part II, of Bell ASB 407-99-26, Revision C, dated February 28, 2002, except this AD does not require you to contact Bell.
(ii) Within 600 hours TIS, but not later than 30 days:
(A) Modify and re-identify each tailboom, P/N 407-030-801-101 as 407-530-014-101, and P/N 407-030-801-105 as 407-530-014-103, by following the Accomplishment Instructions, Parts I and III, of ASB 407-01-48.
(B) Install improved horizontal stabilizer assembly, P/N 407-023-800-ALL, by following Bell Technical Bulletin No. 407-01-33, dated August 29, 2001, except this AD does not require you to contact Bell.
(2) For tailboom, P/Ns 407-530-014-101 and -103, and P/N 407-030-801-107:
(i) Before further flight after the tailboom is modified and re-identified, revise the Airworthiness Limitations section of the maintenance manual by establishing a retirement life of 5,000 hours TIS. Create a component history card or equivalent record and assign a life limit of 5,000 hours TIS by following the Accomplishment Instructions, Part IV, of ASB 407-01-48.
(ii) Within 25 hours TIS or 30 days, whichever occurs first, prepare the tailboom for daily visual checks and recurring inspections and inspect the tailboom for a crack by following the Accomplishment Instructions, Part II, Steps 1.a) through 1.f), of Bell ASB 407-07-80, dated August 27, 2007 (ASB 407-07-80).
(iii) Thereafter, before the first flight of each day, clean the area on the tailboom where paint has been removed at the upper and lower attachment support areas of the horizontal stabilizer and visually check that area of the tailboom for a crack.
(iv) Within 100 hours TIS and thereafter at intervals not to exceed 100 hours TIS, using a 10X or higher power magnifying glass, inspect each tailboom for a loose rivet, a crack, skin corrosion, or any other damage, by following the Accomplishment Instructions, Part IV, Steps 1 through 6, of ASB 407-07-80, except this AD does not require you to contact Bell. If there is corrosion within an allowable tolerance, repair each area of corrosion.
(3) If there is a crack, before further flight, replace the tailboom.
(4) If there is no crack, make sure both of the inspection area surfaces are dry and protect each reworked area with a thin coat of clear coating.
(5) The actions required by paragraphs (f)(1)(i)(A) and (f)(2)(iii) of this AD may be performed by the owner/operator (pilot) holding at least a private pilot certificate and must be entered into the aircraft records showing compliance with this AD in accordance with 14 CFR 43.9 (a)(1) through (4) and 91.417(a)(2)(v). This record must be maintained as required by 14 CFR 91.417, 121.380, or 135.439.
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.
