Airworthiness Directive · Amendment 39-17411 · Stabilizers
The Boeing Company Airplanes
Superseded. A later AD replaced this one: AD 2014-05-30. Comply with the one in force.
(1) This AD applies to all The Boeing Company Model 737-600, -700, -700C, -800, -900, and -900ER series airplanes, certificated in any category.
(2) Installation of Supplemental Type Certificate (STC) ST00830SE (http://rgl.faa. gov/Regulatory_and_Guidance_Library/rgstc.nsf/0/408E012E008616A7862578880060456C?OpenDocument&Highlight=st00830se) does not affect the ability to accomplish the actions required by this AD. Therefore, for airplanes on which STC ST00830SE is installed, a “change in product” alternative method of compliance (AMOC) approval request is not necessary to comply with the requirements of 14 CFR 39.17. For all other AMOC requests, the operator must request approval for an AMOC in accordance with the procedures specified in paragraph (k) of this AD.
We are adopting a new airworthiness directive (AD) for all The Boeing Company Model 737-600, -700, -700C, -800, -900, and -900ER series airplanes. This AD was prompted by reports of an incorrect procedure used to apply the wear and corrosion protective surface coating to attach pins of the horizontal stabilizer rear spar. This AD requires inspecting to determine the part number of the attach pins of the horizontal stabilizer rear spar, and replacing certain attach pins with new, improved attach pins. We are issuing this AD to prevent premature failure of the attach pins, which could cause reduced structural integrity of the horizontal stabilizer to fuselage attachment, resulting in loss of control of the airplane.
For airplanes having line numbers 1 through 3534 inclusive: Before the accumulation of 56,000 total flight cycles, or within 3,000 flight cycles after the effective date of this AD, whichever occurs later, inspect to determine the part number of the attach pins of the horizontal stabilizer rear spar. A review of airplane maintenance records is acceptable in lieu of this inspection if the part number of the attach pin can be conclusively determined from that review.
If, during the inspection required by paragraph (g) of this AD, any horizontal stabilizer rear spar attach pin has P/N 180A1612-3 or 180A1612-4, prior to the accumulation of 56,000 total flight cycles on the pin, or within 3,000 flight cycles after the effective date of this AD, whichever occurs later, replace with a new attach pin having P/N 180A1612-7 or 180A1612-8, respectively, in accordance with the Accomplishment Instructions of Boeing Special Attention Service Bulletin 737-55-1093, dated April 9, 2012.
(1) For airplanes having line numbers 1 through 3534 inclusive: As of the effective date of this AD, no person may install an attach pin of the horizontal stabilizer rear spar having P/N 180A1612-3 or 180A1612-4 on any airplane; unless the actions required by paragraph (g) and (h) of this AD have been done on that airplane.
(2) For airplanes having line numbers 3535 and subsequent: As of the effective date of this AD, no person may install an attach pin of the horizontal stabilizer rear spar having P/N 180A1612-3 or 180A1612-4 on any airplane.
Accomplishment of the actions required by paragraphs (g) and (h) of this AD terminates the requirements of paragraphs (a), (b), (c), (d), and (e) of AD 2004-05-19, Amendment 39-13514 (69 FR 10921, March 9, 2004; corrected April 13, 2004 (69 FR 19313)) for the rear spar attach pins only.
