77-14-14 PIPER: Amendment 39-2965. Applies to Piper Models PA-31 and PA-31-325, Serial Nos. 31-7612064 through 31-7612110, 31-7712001 through 31-7712012, 31-7712014, 31- 7712015, 31-7712017, 31-7712018, 31-7712020 through 31-7712023 and 31-7712025 through 31-7712027; PA-31-350 Serial Nos. 31-7652104 through 31-7652120, 31-7652122, 31-7652124, 31-7652125, 31-7652127, 31-7652129, 31-7652130, 31-7652132 through 31-7652135, 31-7652137, 31-7652139, 31-7652141, 31-7652142, 31-7652145, 31-7652147, 31-7652148, 31- 7652150, 31-7652151, 31-7652153, 31-7652154, 31-7652156, 31-7652157, 31-7652159, 31-7652162 through 31-7652177, 31-7752001, 31-7752002, 31-7752004 through 31-7752006, 31-7752008, 31-7752009, 31-7752011, 31-7752012, 31-7752015, 31-7752019 through 31-7752022, 31-7752027 through 31-7752036, 31-7752038, 31-7752040, 31-7752042, and 31-7752047 through 31-7752049, certificated in all categories.
To prevent possible hazards associated with a defective channel, part number 40358-5,installed in the right wing front spar accomplish the following:
(a) Before further flight, inspect the right wing lower surface from the front spar fuselage attachment diagonally aft to the area of the wheel well for indications of lower wing skin deformation and loose or missing rivets.
(b) Should any of the above-described conditions exist, the aircraft shall not be flown until the damage is assessed and repairs are effected.
(c) If there is no visible damage, (1) on model PA-31-350 install in full view of the pilot a placard that reduces the maximum landing weight to 6650 lb. and visually check area described in paragraph (a) above after each 20 landings; (2) on models PA-31 and PA-31-325, visually check area described in paragraph (a) above after each 20 landings. If there is evidence of damage from the visual check, comply with paragraph (b).
(d) Within the next 50 hours in service after the effective date of this AD unless previously accomplished, alter theinboard end of the right front wing spar in accordance with Piper Kit No. 761 137, Right Wing Front Spar Reinforcement.
(e) Upon incorporating paragraph (d) or equivalent alteration the weight restriction and visual check requirement in paragraph (c) may be dispensed with.
(f) Repairs and equivalent alterations must be approved by the Chief, Engineering and Manufacturing Branch, FAA, Eastern Region.
(g) Upon submission of substantiating data through an FAA Maintenance Inspector, the Chief, Engineering and Manufacturing Branch, FAA, Eastern Region may adjust the compliance time specified in paragraph (d).
Piper Service Bulletin 554 dated March 7, 1977, pertains to this subject.
This amendment becomes effective on July 19, 1977.