Airworthiness Directive · Amendment 39-17379 · Flight controls
The Boeing Company Airplanes
This AD applies to The Boeing Company Model 767-200, -300, -300F, and -400ER series airplanes, certificated in any category; as identified in the service information specified in paragraphs (c)(1), (c)(2), (c)(3), (c)(4), (c)(5), and (c)(6) of this AD.
(1) Boeing Service Bulletin 767-27A0224, Revision 1, dated December 16, 2011.
(2) Boeing Service Bulletin 767-49A0035, Revision 2, dated June 2, 2006.
(3) Boeing Service Bulletin 767-27-0204, Revision 2, dated August 16, 2011.
(4) Boeing Service Bulletin 767-27-0205, Revision 2, dated August 30, 2011.
(5) Boeing Service Bulletins 767-51A0027, Revision 1, dated October 12, 2006.
(6) Boeing Service Bulletin 767-51A0028, Revision 1, dated October 12, 2006.
We are adopting a new airworthiness directive (AD) for certain The Boeing Company Model 767 airplanes. This AD was prompted by reports of stiff operation of the elevator pitch control system and jammed elevator controls. This AD requires replacing pressure seal assemblies; doing repetitive inspections for dirt, loose particles, or blockage of the flanged tube and drain hole for the pressure seals, and corrective action if necessary; replacing the aft air-intake duct assembly with a new or modified assembly and installing a dripshield; and installing gutters on the horizontal stabilizer center section and modifying the side brace fittings. We are issuing this AD to prevent moisture from collecting and freezing on the elevator control system components, which could limit the ability of the flightcrew to make elevator control inputs and result in reduced controllability of the airplane.
For airplanes identified in Boeing Service Bulletin 767-27-0204, Revision 2, dated August 16, 2011; and Boeing Service Bulletin 767-27-0205, Revision 2, dated August 30, 2011: At the applicable time specified in paragraph (g)(1) or (g)(2) of this AD, do a general visual inspection for dirt, loose particles, and blockage of the flanged tube and drain hole for the E1A and E1B elevator control cable aft pressure seals, and all applicable corrective actions, in accordance with the Accomplishment Instructions of Boeing Service Bulletin 767-27-0204, Revision 2, dated August 16, 2011 (for Model 767-200, -300, and -300F series airplanes); or Boeing Service Bulletin 767-27-0205, Revision 2, dated August 30, 2011 (for Model 767-400ER series airplanes). Do all applicable corrective actions before further flight. Repeat the inspection thereafter at intervals not to exceed 24 months.
(1) For airplanes on which Boeing Service Bulletin 767-27A0219 has been done as of the effective date of this AD: Within 24 months after the effective date of this AD.
(2) For airplanes on which Boeing Service Bulletin 767-27A0219 has not been done as of the effective date of this AD: Do the inspection at the time specified in paragraph (g)(2)(i) or (g)(2)(ii) of this AD, whichever occurs later.
(i) Within 24 months after the effective date of this AD.
(ii) Within 24 months since the date of issuance of the original airworthiness certificate or the date of issuance of the original export certificate of airworthiness.
For Group 1, Configuration 1 and 2 airplanes; Group 2, Configuration 1 airplanes; and Group 4, Configuration 1 and 2 airplanes; as identified in Boeing Service Bulletin 767-27A0224, Revision 1, dated December 16, 2011: Within 24 months after the effective date of this AD, replace the two existing pressure seal assemblies for the left elevator control cables at the aft pressure bulkhead, in accordance with the Accomplishment Instructions of Boeing Service Bulletin 767-27A0224, Revision 1, dated December 16, 2011, except as provided by paragraphs (k)(9), (k)(10), (k)(11), and (k)(12) of this AD. Accomplishing this replacement terminates the inspections required by paragraph (g) of this AD.
For airplanes identified in Boeing Service Bulletin 767-49A0035, Revision 2, dated June 2, 2006: Within 18 months after the effective date of this AD, replace the aft air-intake duct assembly with a new or modified aft air-intake duct assembly and install a dripshield, in accordance with the Accomplishment Instructions of Boeing Service Bulletin 767-49A0035, Revision 2, dated June 2, 2006, except as provided by paragraphs (k)(1) and (k)(8) of this AD.
For airplanes identified in Boeing Service Bulletin 767-51A0027, Revision 1, dated October 12, 2006; and Boeing Service Bulletin 767-51A0028, Revision 1, dated October 12, 2006: Within 60 months after the effective date of this AD, install gutters on the horizontal stabilizer center section, and modify the side brace fittings, including doing a dye penetrant or high frequency eddy current inspection for cracking and damage of the drain hole and all applicable corrective actions, in accordance with the Accomplishment Instructions of Boeing Service Bulletin 767-51A0027, Revision 1, dated October 12, 2006 (for Model 767-200, -300, and -300F series airplanes); or Boeing Service Bulletin 767-51A0028, Revision 1, dated October 12, 2006 (for Model 767-400ER series airplanes); except as provided by paragraphs (k)(2), (k)(3), (k)(4), (k)(5), (k)(6), and (k)(7) of this AD.
(1) Where step 1 of Figure 4 of Boeing Service Bulletin 767-49A0035, Revision 2, dated June 2, 2006, specifies installing the forward air-intake duct, that installation is not required by this AD.
(2) Where Boeing Service Bulletin 767-51A0027, Revision 1, dated October 12, 2006; and Boeing Service Bulletin 767-51A0028, Revision 1, dated October 12, 2006; specify to contact Boeing for appropriate action: Before further flight, repair using a method approved in accordance with the procedures specified in paragraph (n) of this AD.
(3) Where step 8 in Figures 6 and 10 of Boeing Service Bulletin 767-51A0027, Revision 1, dated October 12, 2006; and Boeing Service Bulletin 767-51A0028, Revision 1, dated October 12, 2006; specify hydraulic hose, part number (P/N) AS115-08D0274, the correct part number is AS115-08D0280.
(4) For steps 4, 8, and 12 in Figures 6 and 10 of Boeing Service Bulletin 767-51A0027, Revision 1, dated October 12, 2006; and Boeing Service Bulletin 767-51A0028, Revision 1, dated October 12, 2006: Hydraulic hose, P/N AS115-08K0280, is an option to P/N AS115-08D0280.
(5) For steps 2, 6, and 10 in Figures 6 and 10 of Boeing Service Bulletin 767-51A0027, Revision 1, dated October 12, 2006; and Boeing Service Bulletin 767-51A0028, Revision 1, dated October 12, 2006: Hydraulic hose, P/N AS115-06K0274, is an option to P/N AS115-06D0274.
(6) Steps 3.B.16 and 3.B.17 of Boeing Service Bulletin 767-51A0027, Revision 1, dated October 12, 2006; and Boeing Service Bulletin 767-51A0028, Revision 1, dated October 12, 2006; are not required by this AD.
(7) Where note (d) of Figure 8 of Boeing Service Bulletin 767-51A0027, Revision 1, dated October 12, 2006; and Boeing Service Bulletin 767-51A0028, Revision 1, dated October 12, 2006; specifies to “install collars on the upper surface of the gutter,” this AD requires that operators install these bolts with the bolt heads either up or down provided that the bolt head direction prevents interference between the collars and the hydraulic lines.
(8) Where Boeing Service Bulletin 767-49A0035, Revision 2, dated June 2, 2006, specifies installing a new aft air-intake duct assembly on the first airplane in each operator's fleet and installing a reworked aft air-intake duct assembly on all remaining airplanes in each operator's fleet, this AD requires installing either a new or reworked aft air-intake duct assembly on all airplanes.
(9) For Group 4 airplanes, as identified in Boeing Service Bulletin 767-27A0224, Revision 1, dated December 16, 2011: Where Figures 7 through 10 of Boeing Service Bulletin 767-27A0224, Revision 1, dated December 16, 2011, specify to replace the seal plate assembly, this AD allows replacing the configuration having two seal plates, P/Ns 255T4847-1 and 65-28174-1, with the configuration having one seal plate, P/N 255T4847-5.
(10) For Group 1 through 3 airplanes, as identified in Boeing Service Bulletin 767-27A0224, Revision 1, dated December 16, 2011: Where Figures 1 and Figures 4 through 6 of Boeing Service Bulletin 767-27A0224, Revision 1, dated December 16, 2011, specify to replace the seal plate, this AD allows replacing the configuration having one seal plate, P/N 255T4847-5 with the configuration having two seal plates, P/Ns 255T4847-1 and 65-28174-1.
(11) Where steps 8 and 9 of Figure 4 and steps 8 and 9 of Figure 8 of Boeing Service Bulletin 767-27A0224, Revision 1, dated December 16, 2011, specify installing clamp P/N AN735-16, this AD allows, for airplanes having increased diameter of the flanged tube due to a repair, installation of a clamp, P/N AN735-(), that has a larger diameter than P/N AN735-16.
(12) Where steps 1 and 4 of Figure 6 and steps 1 and 4 of Figure 10 of Boeing Service Bulletin 767-27A0224, Revision 1, dated December 16, 2011, specify installing bolts, this AD allows installation of bolts having P/N BACB30NT3K(), BACB30LK3-(), BACB30ZG3-(), or NAS623-3-().
For Group 1, Configuration 3 and 4 airplanes; Group 2, Configuration 2 and 3 airplanes; Group 3 airplanes; and Group 4, Configuration 3 and 4 airplanes; as identified in Boeing Service Bulletin 767-27A0224, Revision 1, dated December 16, 2011: Replacing the two existing pressure seal assemblies for the left elevator control cables at the aft pressure bulkhead, in accordance with the Accomplishment Instructions of Boeing Service Bulletin 767-27A0224, Revision 1, dated December 16, 2011, except as provided by paragraphs (k)(9), (k)(10), (k)(11), and (k)(12) of this AD, terminates the inspections required by paragraph (g) of this AD.
The aircraft, engines and makers this AD names, by the model designations in its text. A model listed here may still be outside the AD's serial ranges.
Aircraft
