AD 79-26-04

79-26-04 PIPER AIRCRAFT CORPORATION: Amendment 39-3642. Applies to the following Model PA-32RT-300 and PA-32RT-300T series airplanes, certificated in all categories:

PA-32RT-300 Lance II 32R-7885001 to 32R-7885025 Inclusive

32R-7885027 to 32R-7885261 Inclusive

32R-7885263 to 32R-7885285 Inclusive

32R-7985001 to 32R-7985035 Inclusive

32R-7985037 to 32R-7985045 Inclusive

32R-7985047 to 32R-7985059 Inclusive

32R-7985062, 32R-7985064,

32R-7985066, 32R-7985067,

32R-7985069 to 32R-7985076 Inclusive

32R-7985078,

32R-7985083 to 32R-7985085 Inclusive

32R-7985088 to 32R-7985090 Inclusive

32R-7985092 to 32R-7985097 Inclusive

32R-7985101,

32R-7985103 to 32R-7985105 PA-32RT-300T Turbo Lance lI 32R-7887001 to 32R-7887222 Inclusive

32R-7887224 to 32R-7887226 Inclusive

32R-7887228 to 32R-7887237 Inclusive

32R-7887239 to 32R-7887243 Inclusive

32R-7887245 to 32R-7887254 Inclusive

32R-7887256 to 32R-7887261 Inclusive32R-7887263,

32R-7887265 to 32R-7887289 Inclusive

32R-7987001, 32R-7987002

32R-7987004 to 32R-7987011 Inclusive

32R-7987013, 32R-7987014,

32R-7987016, 32R-7987017,

32R-7987019, 32R-7987020,

32R-7987024 to 32R-7987028 Inclusive

32R-7987029, 32R-7987030,

32R-7987032, 32R-7987034,

32R-7987035, 32R-7987038,

32R-7987039, 32R-7987041,

32R-7987042, 32R-7987044,

32R-7987046,

32R-7987049 to 32R-7987051 Inclusive

32R-7987054 to 32R-7987058 Inclusive

32R-7987060, 32R-7987066,

32R-7987068 to 32R-7987070 Inclusive

32R-7987072, 32R-7987073,

32R-7987075, 32R-7987076,

32R-7987078 to 32R-7987080 Inclusive

32R-7987082 to 32R-7987086 Inclusive

32R-7987088, 32R-7987089,

32R-7987091, 32R-7987094,

32R-7987096 to 32R-7987099 Inclusive

32R-7987101, 32R-7987102,

32R-7987104,

32R-7987107 to 32R-7987115 Inclusive

32R-7987117, 32R-7987119,

32R-7987122, 32R-7987124,

32R-7987125, 32R-7987126.Compliance as prescribed in the body of the AD.

To prevent initiation and/or growth of rudder skin cracks, with resulting possible weakening of rudder structural integrity, accomplish the following, unless already accomplished:

a. Within the next 25 hours time-in-service after the effective date of this AD, and at intervals not to exceed 25 hours time in service, visually check the area along the skin beads at the trailing edge of the rudder for cracks. This check may be accomplished by the pilot.

NOTE: A maintenance record entry showing compliance with these repetitive visual checks is required.

b. If crack(s) are found, repair within the next 10 hours time in service in accordance with the instructions contained in Piper Kit Part Number 763 940V, or in an equivalent manner approved by the Chief, Engineering and Manufacturing Branch, FAA Southern Region.

c. If no crack(s) are found during the checks required by paragraph a, modify the rudder within thenext 100 hours time in service after the effective date of this AD in accordance with the instructions contained in Piper Kit Part Number 763 936V, or in an equivalent manner approved by the Chief, Engineering and Manufacturing Branch, FAA Southern Region.

d. Verify that the rudder balance, after repair or modification, is within the limits established in the Piper Lance II Service Manual.

e. Compliance with paragraphs b or c, and d, above terminates the repetitive checks required in paragraph a above.

f. Upon submission of substantiating data through an FAA Aviation Safety Inspector, the Chief, Engineering and Manufacturing Branch, FAA Southern Region, may adjust the repair or modification compliance time.

Piper Service Letter No. 882 also deals with this subject.

This amendment is effective January 7, 1980.