AD 80-20-05

80-20-05 PIPER AIRCRAFT CORPORATION: Amendment 39-3926. Applies to the following PA-32RT-300T model serial numbers, certificated in all categories:

32R-7887001 through 32R-7887222, 32R-7887224 through 32R-7887226, 32R-7887228 through 32R-7887237, 32R-7887239 through 32R-7887243, 32R-7887246 through 32R-7887254, 32R-7887256 through 32R-7887261, 32R-7887263, 32R-7887265 through 32R-7887289, 32R-7987001, 32R-7987002 and 32R-7987004 through 32R-7987011, 32R-7987013, 32R-7987014 and 32R-7987016 through 32R-7987020, 32R-7987024, 32R-7987028 through 32R-7987030, 32R-7987032, 32R-7987034, 32R-7987035, 32R-7987038, 32R-7987039, 32R-7987041, 32R-7987042, 32R-7987044 and 32R-7987046, 32R-7987049 through 32R-7987051, 32R-7987054 through 32R-7987058, 32R-7987060, 32R-7987066 and 32R-7987068 through 32R-7987070, 32R-7987072 through 32R-7987073, 32R-7987075, 32R-7987076 and 32R-7987078 through 32R-7987080, 32R-7987082 through 32R-7987086, 32R-7987088, 32R-7987089, 32R-7987091, 32R-7987094, 32R-7987096 through 32R-7987099, 32R-7987101, 32R-7987102, 32R-7987104, 32R-7987107 through 32R-7987115, 32R-7987117 through 32R-7987119, 32R-7987123

NOTE: The requirements of emergency airworthiness directive issued June 14, 1979, were found to be not applicable to the following serial numbers:

32R-7887223, 32R-7887227, 32R-7887238, 32R-7887244, 32R-7887245, 32R-7887255, 32R-7887262, 32R-7887264, 32R-7987003, 32R-7987012, 32R-7987015, 32R-7987021, 32R-7987022, 32R-7987023, 32R-7987025, 32R-7987026, 32R-7987027, 32R-7987031, 32R-7987033, 32R-7987036, 32R-7987037, 32R-7987040, 32R-7987043, 32R-7987045, 32R-7987047, 32R-7987048, 32R-7987052, 32R-7987053, 32R-7987059, 32R-7987061, 32R-7987062, 32R-7987063, 32R-7987064, 32R-7987065, 32R-7987071, 32R-7987074, 32R-7987077, 32R-7987081, 32R-7987087, 32R-7987090, 32R-7987092, 32R-7987093, 32R-7987095, 32R-7987100, 32R-7987103, 32R-7987105, 32R-7987106, 32R-7987116,32R-7987120, 32R-7987121, 32R-7987122, 32R-7987124, 32R-7987125, 32R-7987126.

Compliance is required within the next 10 hours time in service after the effective date of this AD, unless already accomplished.

To prevent a possible turbocharger exhaust coupling failure, which could result in a fire hazard, accomplish the following:

(a) Gain access to turbocharger exhaust system.

(b) Remove the turbocharger exhaust coupling P/N 556 108 and tailpipe P/N 98705- 2.

(c) Using either a dye penetrant method or a 10-power magnifying glass, inspect coupling, coupling bolt, tailpipe and tailpipe flange for cracks, deformation or damage.

(d) Measure width across inside opening of retainer segments of coupling. Maximum allowable dimension is .350 in (See Figure 1)

(e) Measure thickness of tailpipe flange at apex. Dimension required is .096 plus or minus .005 inch. (See Figure 1)

(f) If flange dimension is under the tolerance shown in (e) above, replace tailpipe. If over tolerance, rework the flange mating surface to dimensions in (e) above, provided .005 inch flatness is maintained or replace with serviceable part.

(g) Replace any exhaust system parts found cracked, deformed or damaged during the inspection required above with a serviceable part, before further flight.

(h) Reinstall serviceable parts as follows:

(1) Assure turbocharger and tailpipe flange are properly aligned. Tap coupling gently to distribute band tension while tightening coupling nut.

(2) Torque coupling nut to 40-50 inch pounds and safety wire.

(i) Make appropriate maintenance record entry.

An equivalent method of compliance may be approved by the Chief, Engineering and Manufacturing Branch, Federal Aviation Administration, Southern Region, P.O. Box 20636, Atlanta, Georgia 30320.

This amendment is effective upon publication in the Federal Register as to all persons, except those persons to whom it was made immediately effectiveby priority mail, issued June 14, 1979, which contained this amendment.

FIGURE 1 AD 80-20-05