82-23-02 BEECH: Amendment 39-4484. Applies to Models 65-90 and 65-A90 (S/Ns LJ-1 through LJ-317) and B90 (S/Ns LJ-318 through LJ-501), except those airplanes having reinforced elevators per Beech Service Instructions No. 0333-131, Revision II, or P/N 50- 610000-349 LH and -350 RH aluminum elevators (reference Kit Nos. 90-4061 S, 90-4062 S, 90- 4062-1 S).
COMPLIANCE: Required as indicated, unless already accomplished.
To prevent elevator spar failures and possible loss of elevator control, accomplish the following:
(a) On all affected Models 65-90 and those 65-A90 airplanes which do not have elevator overhang balance horns installed per Beech Kit No. 90-4029 (9.5-inch outboard end overhang, part of Kit Nos. 90-4031 M, 90-4031-1 M, and 90-4035 M) prior to attaining 2,100 hours time-in-service (TIS) on airplanes having less than 2,000 hours TIS, or within 100 hours TIS after the effective date of this AD on airplanes having 2,000 or more hours TIS and at intervals notexceeding 500 hours TIS thereafter:
(1) Incorporate an inspection port, check the elevator hinge point alignment, and, if necessary, correct it in accordance with Beech Service Instructions No. 0450-133, Revision I (initial inspection only).
(2) Visually inspect the elevator spar at the outboard hinge point for cracks in accordance with Beech Service Instructions No. 0450-133, Revision I (initial and recurring inspection).
(b) On all affected Model B90 and those Model 65-A90 airplanes which have elevator overhang balance horns per Beech Kit No. 90-4029 (see (a) above for description) prior to attaining 600 hours TIS on airplanes having less than 500 hours TIS, or within 100 hours TIS after the effective date of this AD on airplanes having 500 or more hours TIS and at intervals not exceeding 200 hours TIS thereafter:
(1) Incorporate an inspection port, check the elevator hinge point alignment, and, if necessary, correct it in accordance with Beech Service Instructions No. 0423-133 (initial inspection only).
(2) Visually inspect the elevator spar at the outboard hinge point for cracks in accordance with Beech Service Instruction No. 0423-133 (initial and recurring inspection).
(c) Prior to further flight, repair or replace with serviceable parts any components found cracked during the inspections specified in paragraph (a) or (b).
(d) Airplanes may be flown in accordance with FAR 21.197 to a base where the inspections and repair/replacement can be performed.
(e) Intervals between repetitive inspections required by this AD may be increased up to 10 percent to allow them to coincide with other scheduled maintenance on the airplane.
(f) An equivalent method of compliance with this AD may be used if approved by the Manager, Wichita Aircraft Certification Office, Room 238, Terminal Building 2299, Mid- Continent Airport, Wichita, Kansas 67209, telephone (316) 269-7000.
This AD supersedes AD 71-14-04, Amendment 39-1241 (36 FR 12842, July 8, 1971).
This Amendment 39-4484 becomes effective on November 8, 1982.