Airworthiness directives › 2015-26-07
AD 2015-26-07 Airworthiness Directives; The Boeing Company Airplanes
Models named: 767-200, -300, -300F series. Read the applicability below — it usually turns on serial or part numbers too.
Applicability*9
(1) This AD applies to The Boeing Company Model 767-200, -300, -300F series airplanes, certificated in any category, as identified in Boeing Alert Service Bulletin 767-53A0261, dated August 12, 2014. (2) Installation of Supplemental Type Certificate (STC) ST01920SE ( http://rgl.faa.gov/Regulatory_and_Guidance_Library/rgstc.nsf/0/59027F43B9A7486E86257B1D006591EE ) does not affect the ability to accomplish the actions required by this AD. Therefore, for airplanes on which STC ST01920SE ( http://rgl.faa.gov/Regulatory_and_Guidance_Library/rgstc.nsf/0/59027F43B9A7486E86257B1D006591EE ) 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.
Compliance
Comply with this AD within the compliance times specified, unless already done.
Required actions
For airplanes identified in Boeing Alert Service Bulletin 767-53A0261, dated August 12, 2014: Do the actions specified in paragraph (g)(1) or (g)(2) of this AD, in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 767-53A0261, dated August 12, 2014. Signs of corrosion include, but are not limited to, sealant cracks, sealant bulging, powder residue, and cracked barrel nuts. (1) At the applicable time specified in paragraph 1.E., “Compliance,” of Boeing Alert Service Bulletin 767-53A0261, dated August 12, 2014, except as provided by paragraph (i) of this AD: Do internal and external detailed inspections of the barrel nuts and sealant for signs of corrosion, and do a torque check of the vertical stabilizer attachment bolts for loose barrel nuts. (i) If corrosion or any loose barrel nut is found at any attachment point location, before further flight, replace the barrel nut with a new Inconel barrel nut. (ii) If no corrosion or loose barrel nut is found at any attachment point location, do the actions specified in paragraphs (g)(1)(ii)(A) and (g)(1)(ii)(B) of this AD. (A) Repeat the inspections and torque check thereafter at intervals not to exceed 18 months until the replacement specified in paragraph (g)(1)(ii)(B) of this AD is done at that attachment point location. (B) Within 36 months after the effective date of this AD, replace all barrel nuts with new Inconel barrel nuts. (2) At the applicable time specified in paragraph 1.E., “Compliance,” of Boeing Alert Service Bulletin 767-53A0261, dated August 12, 2014, except as provided by paragraph (i) of this AD: Do a magnetic check to identify H-11 steel barrel nuts. (i) If any H-11 steel barrel nut is found at any attachment point location, before further flight, do an internal and external detailed inspection of the barrel nut holes and sealant for signs of corrosion, and do a torque check of the vertical stabilizer attachment bolts for loose barrel nuts. (A) If corrosion or any loose barrel nut is found, before further flight, replace the barrel nut with a new Inconel barrel nut. (B) If no corrosion or loose barrel nut is found, do the actions specified in paragraphs (g)(2)(i)(B)( 1 ) and (g)(2)(i)(B)( 2 ) of this AD. ( 1 ) Repeat the inspections and torque check thereafter at intervals not to exceed 18 months until the replacement specified in paragraph (g)(2)(i)(B)( 2 ) of this AD is done at that attachment point location. ( 2 ) Within 36 months after the effective date of this AD, replace all H-11 steel barrel nuts with new Inconel barrel nuts. (ii) If no H-11 steel barrel nut is found at all attachment point locations, no further work is required by this paragraph.
Unsafe condition
This AD was prompted by a finding that certain barrel nuts installed at the vertical fin may be subject to stress corrosion and cracking. We are issuing this AD to detect and correct corroded and loose barrel nuts that attach the vertical fin to body section 48; this condition could result in reduced structural integrity of the vertical fin attachment joint, loss of the vertical fin, and consequent loss of controllability of the airplane.
Affected ADs
None.
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