Airworthiness Directive · Amendment 39-17419 · Stabilizers
The Boeing Company Airplanes
This AD applies to The Boeing Company Model 777-200, -200LR, -300, and -300ER series airplanes, certificated in any category, as identified in Boeing Alert Service Bulletin 777-55A0016, Revision 1, dated August 25, 2011.
We are superseding an existing airworthiness directive (AD) that applies to all The Boeing Company Model 777-200, -200LR, -300, and -300ER series airplanes. That AD currently requires repetitive inspections for cracking of the elevator actuator fittings. This new AD requires, for previously modified airplanes, repetitive inspections for movement of the fittings or fastener heads, and eventual replacement of certain bolts (including related investigative and corrective actions if necessary). For all airplanes, this replacement, with corrected torque values, would terminate the requirements of the existing AD. This new AD also removes certain airplanes from the applicability. This AD was prompted by the manufacturer's development of a modification that was approved as an optional terminating action to the existing AD's required repetitive inspections. We have been advised that the modification procedures include certain incorrect torque values. We are issuing this AD to detect and correct a cracked actuator fitting or incorrectly installed bolts to the actuator fitting, which could lead to the elevator becoming detached and unrestrained, and a consequent unacceptable flutter condition and loss of control of the airplane.
This paragraph restates the inspections and corrective actions required by paragraph (f) of AD 2007-26-05, Amendment 39-15307 (72 FR 71212, December 17, 2007), with revised service information.
(1) Except as provided by paragraph (j)(2) of this AD: Do all inspections and actions described in paragraphs (g)(1) and (g)(2) of this AD, in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 777-55A0015, dated April 19, 2007; or Boeing Service Bulletin 777-55A0015, Revision 3, dated November 24, 2009. At the applicable time specified in paragraph 1.E., “Compliance,” of Boeing Alert Service Bulletin 777-55A0015, dated April 19, 2007, except as provided by paragraph (g)(3) of this AD, do an initial dye penetrant or high frequency eddy current (HFEC) inspection for cracking of the elevator actuator fittings, and, thereafter, do repetitive dye penetrant, HFEC, or detailed inspections at the applicable times specified in paragraph 1.E., “Compliance,” of Boeing Alert Service Bulletin 777-55A0015, dated April 19, 2007. As of the effective date of this AD, Boeing Service Bulletin 777-55A0015, Revision 3, dated November 24, 2009, must be used to accomplish the actions required by this paragraph.
(2) Before further flight, replace any fitting found to be cracked during any inspection required by paragraph (g)(1) of this AD with a new fitting having the same part number, or an optional part number, as identified in Boeing Alert Service Bulletin 777-55A0015, dated April 19, 2007; or Boeing Service Bulletin 777-55A0015, Revision 3, dated November 24, 2009; except as provided by paragraph (j)(2) of this AD. Thereafter, do initial and repetitive inspections of the replacement fitting at the time specified in paragraph 1.E., “Compliance,” of Boeing Alert Service Bulletin 777-55A0015, dated April 19, 2007. As of the effective date of this AD, Boeing Service Bulletin 777-55A0015, Revision 3, dated November 24, 2009, must be used to accomplish the actions required by this paragraph.
(3) Where Boeing Alert Service Bulletin 777-55A0015, dated April 19, 2007, specifies a compliance time after the date on that service bulletin, this AD requires compliance within the specified compliance time after January 22, 2008 (the effective date of AD 2007-26-05, Amendment 39-15307 (72 FR 71212, December 17, 2007)).
For airplanes on which the elevator actuator fitting assemblies have been replaced using the fastener torque values specified in Boeing Alert Service Bulletin 777-55A0016, dated October 27, 2009: Within 180 days after the effective date of this AD, do a detailed inspection of the elevator actuator fitting assemblies to detect discrepancies (including indications of fastener head movement and fitting movement along the spar web), in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 777-55A0016, Revision 1, dated August 25, 2011, except as provided by paragraph (j)(2) of this AD.
(1) If no discrepancy is detected, do the actions specified in paragraphs (h)(1)(i) and (h)(1)(ii) of this AD.
(i) Repeat the inspection thereafter at intervals not to exceed 90 days or 360 flight cycles, whichever occurs first, until the actions specified in paragraph (h)(1)(ii) of this AD are done.
(ii) Within 4,200 flight cycles or 750 days after the effective date of this AD, whichever occurs first, replace the 12 bolts common to the elevator actuator fitting and the spar web, and do all applicable related investigative and corrective actions, in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 777-55A0016, Revision 1, dated August 25, 2011, except as provided by paragraphs (j)(1) and (j)(2) of this AD. Do all applicable related investigative and corrective actions before further flight. The replacement of all 12 bolts in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 777-55A0016, Revision 1, dated August 25, 2011, terminates the requirements of paragraphs (g) and (h) of this AD for that fitting only.
(2) If any discrepancy is detected, before further flight, replace the 12 bolts common to the elevator actuator fitting and the spar web using new parts, and do all applicable related investigative and corrective actions, in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 777-55A0016, Revision 1, dated August 25, 2011, except as provided by paragraphs (j)(1) and (j)(2) of this AD. Do all applicable related investigative and corrective actions before further flight. The replacement of all 12 bolts in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 777-55A0016, Revision 1, dated August 25, 2011, terminates the requirements of paragraphs (g) and (h) of this AD for that fitting only.
For airplanes on which the elevator actuator fitting assemblies have not been replaced as specified in Boeing Alert Service Bulletin 777-55A0016, dated October 27, 2009: Replacement of these fitting assemblies with new parts, in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 777-55A0016, Revision 1, dated August 25, 2011, except as provided by paragraphs (j)(1) and (j)(2) of this AD, terminates the requirements of paragraphs (g) and (h) of this AD.
(1) If any discrepancy or cracking is found during any inspection required by this AD, and Boeing Alert Service Bulletin 777-55A0016, Revision 1, dated August 25, 2011, specifies 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.
(2) Where the service bulletins identified in paragraphs (j)(2)(i), (j)(2)(ii), and (j)(2)(iii) of this AD specify to “Put airplane back in a serviceable condition,” this AD does not require that action.
(i) Boeing Alert Service Bulletin 777-55A0015, dated April 19, 2007.
(ii) Boeing Service Bulletin 777-55A0015, Revision 3, dated November 24, 2009.
(iii) Boeing Alert Service Bulletin 777-55A0016, Revision 1, dated August 25, 2011.
Replacing the elevator with a new elevator terminates the requirements of paragraphs (g) and (h) of this AD, provided that the elevator actuator fitting configuration on the new elevator complies with the modification and bolt torque values defined in the Accomplishment Instructions of Boeing Alert Service Bulletin 777-55A0016, Revision 1, dated August 25, 2011.
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
