87-04-03 MITSUBISHI: Amendment 39-5527. Applies to Models MU-2B, MU-2B-10, MU-2B-15, MU-2B-20, MU-2B-25, MU-2B-26, MU-2B-26A, MU-2B-30, MU-2B-35, MU-2B- 36, MU-2B-36A, MU-2B-40, MU-2B-60 airplanes (Serial Numbers (S/Ns) 008 through 457 inclusive (incl.), 501 through 799 incl., 1501 through 1566 incl. with or without the SA suffix), certificated in any category. (Serial numbers with "SA" suffix designate those MU-2B airplanes certificated in the United States of America under Type Certificate (TC) A10SW, and those serial numbers without "SA" suffix designate those MU-2B airplanes certificated in Japan under TC A2PC.)
Compliance: Required as indicated in the body of the AD, unless previously accomplished.
To preclude failure of flap flexible shaft Part Numbers (P/N) RY25-1, or 8022Y-OC- 97.00, or 8022Y-OC-97.50, or 035A-961001-3, and potential differential flap operation, accomplish the following:
(a) For flap flexible shafts:
(1) With less than 1,000 hours of time-in-service (TIS) on the effective date of this AD:
(i) Within the next 100 hours of TIS, seal the fitting and the connection area of the flap flexible shaft in accordance with "INSTRUCTIONS" of MHI MU-2 Service Bulletin (S/B) No. 198 dated February 13, 1985, or "ACCOMPLISHMENT INSTRUCTIONS" of MAI MU-2 S/B SB051/27-007 dated February 1, 1985, as applicable.
(ii) Prior to the accumulation of 1,100 hours total TIS of the flap flexible shaft, perform torque inspection of the flap flexible shaft in accordance with the MHI MU-2 S/B No. 198, or MAI MU-2 S/B SB051/27-007, as applicable.
(A) If the torque value is less than 1.2 in-lbs (1.4 kg-cm) or less, in both clockwise and counter clockwise rotation, seal the flexible shaft in accordance with "INSTRUCTIONS" OF MHI MU-2 S/B NO. 198 or "ACCOMPLISHMENT INSTRUCTIONS" of MAU MU-2 S/B SB051/27-007, as applicable and return the airplane to service.
(B) If the torque value is greater than 1.2 in-lbs (1.4 kg-cm) in any direction of rotation, before further flight, remove flap flexible shaft and replace this shaft with a serviceable shaft, P/N 8022Y-OC-97.00, or 8022Y-OC-97.50 or 035A-961001-3 or FAA approved equivalent, in accordance with paragraph (b) of this AD, and return the airplane to service.
(2) With 1,000 or more hours of TIS on the effective date of this AD: Within 100 additional hours TIS perform the torque inspection in accordance with MHI MU-2 S/B No. 198, or MAI MU-2 S/B SB051/27-007, as applicable.
(i) If the torque value is 1.2 in-lbs (1.4 kg-cm) or less, in both clockwise and counter clockwise rotation, seal the flexible shaft in accordance with "INSTRUCTIONS" of MHI MU-2 S/B No. 198 or "ACCOMPLISHMENT INSTRUCTIONS" of MAI MU-2B S/B SB051/27-007, as applicable and return the airplane to service.
(ii) If the torque value is greater than 1.2 in-lbs (1.4 kg-cm) in any direction of rotation, before further flight, remove flap flexible shaft and replace this shaft with a serviceable shaft, P/N 8022Y-OC-97.00, or 8022Y-OC-97.50 or 035A-961001-3 or FAA approved equivalent, in accordance with paragraph (b) of this AD, and return the airplane to service.
(b) Prior to installing a serviceable replacement flexible shaft, seal the part in accordance with MHI MU-2 S/B No. 198 or MAI MU-2 S/B SB051/27-007, as applicable.
(c) Within 100 hours of TIS after the effective date of this AD, remove and do not reinstall the clamp at W.S. 2590 and ensure that the flap flexible shaft is installed so as to establish that no bend radius throughout the length of the shaft between Wing Station (W.S.) 2370 and W.S. 2910 is less than 8.7 inches (220 millimeters).
(d) Special flight permits may be issued in accordance with FAR 21.197 and FAR 21.199 to ferry aircraft to a maintenance base in order to comply with the requirements of this AD.
(e) An equivalent method of compliance with this AD may be used on the MHI airplanes, if approved by the Manager, Western Aircraft Certification Office, ANM-170W, Federal Aviation Administration, P.O. Box 92007, Worldway Postal Center, Los Angeles, California 90009-2007, and on the MAI airplanes, if approved by the Manager, FAA, Wichita Aircraft Certification Office, 1801 Airport Road, Room 100, Mid-Continent Airport, Wichita, Kansas 67209.
All persons affected by this directive may obtain copies of the documents referred to herein upon request to Mitsubishi Heavy Industries, Ltd., 10, Oye-Cho, Minato-ku, Nagoya, Japan or Beech Aircraft Corporation, 9709 East Central, P.O. Box 85, Wichita, Kansas 67201, Attention: Manager, Publications; or FAA, Office of the Regional Counsel, Room 1558, 601 East 12th Street, Kansas City, Missouri 64106.
This amendment supersedes AD 74-11-02 (Amendment 39-1846 (39 FR 17220) as amended by Amendment 39-2269 (40 FR 30464)) and AD 75-02-01 (Amendment 39-2059 (39 FR 44740) as amendment by Amendment 39-2269 (40 FR 30464).
This amendment becomes effective March 7, 1987.