Source: https://www.federalregister.gov/documents/2012/02/09/2012-2976/airworthiness-directives-the-boeing-company-airplanes
Timestamp: 2017-08-24 10:03:44
Document Index: 462593411

Matched Legal Cases: ['§\u200939', 'art 1', 'art 2', 'art 3', 'art 3', 'art 3', 'art 3', 'art 3']

A Proposed Rule by the Federal Aviation Administration on 02/09/2012
We must receive comments on this proposed AD by March 26, 2012.
77 FR 6685
6685-6688 (4 pages)
Docket No. FAA-2012-0108
Directorate Identifier 2011-NM-049-AD
2012-2976
FAA-2012-0108
2011-NM-049-AD The Boeing Company Model 767 airplanes
U.S. DOT/FAA - Material Not Included in Airworthiness...
Restatement of Certain Requirements of AD 2003-13-01, Amendment 39-13201 (68 FR 37402, June 24, 2003), With Revised Service Information
(h) Follow-on/Corrective Actions
(i) Exceptions to Service Bulletin Procedures
(k) Part Installation
(l) Credit for Actions Accomplished in Accordance With Previous Service Information
(m) Initial Inspection
(n) Repetitive Inspections
(o) Optional Terminating Action
(p) Credit for Actions Accomplished in Accordance with Previous Service Information
https://www.federalregister.gov/d/2012-2976 https://www.federalregister.gov/d/2012-2976
We propose to supersede an existing airworthiness directive (AD) that applies to certain The Boeing Company Model 767 airplanes. The existing AD currently requires an inspection to detect cracks and fractures of the outboard hinge fitting assemblies on the trailing edge of the inboard main flap, and follow-on and corrective actions if necessary. For certain airplanes, the existing AD also requires a one-time inspection to determine if a tool runout option has been performed in the area. Since we issued that AD, we have received reports of hinge assembly fractures found before the currently-required inspection cycle compliance times on certain airplanes. This proposed AD reduces compliance times for Model 767-400ER series airplanes. In addition, this proposed AD would revise the applicability to include an additional airplane. We are proposing this AD to prevent the inboard aft flap from separating from the wing and potentially striking the airplane, which could result in damage to the surrounding structure and potential personal injury.
For service information identified in this AD, contact Boeing Commercial Airplanes, Attention: Data & Services Management, P.O. Box 3707, MC 2H-65, Seattle, Washington 98124-2207; telephone 206-544-5000, extension 1; fax 206-766-5680; email me.boecom@boeing.com; Internet https://www.myboeingfleet.com. You may review copies of the referenced service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, Washington. For information on the availability of this material at the FAA, call 425-227-1221.
Berhane Alazar, Aerospace Engineer, Airframe Branch, ANM-120S, FAA, Seattle Aircraft Certification Office, 1601 Lind Avenue SW., Renton, Washington 98057-3356; phone: 425-917-6577; fax: 425-917-6590; email: berhane.alazar@faa.gov.
We invite you to send any written relevant data, views, or arguments about this proposed AD. Send your comments to an address listed under the ADDRESSES section. Include “Docket No. FAA-2012-0108; Directorate Identifier 2011-NM-049-AD” at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of this proposed AD. We will consider all comments received by the closing date and may amend this proposed AD because of those comments.
On June 16, 2003, we issued AD 2003-13-01, Amendment 39-13201 (68 FR 37402, June 24, 2003), for certain Model 767 airplanes. That AD requires an inspection to detect cracks and fractures of the outboard hinge fitting assemblies on the trailing edge of the inboard main flap, and follow-on and corrective actions if necessary. For certain airplanes, that AD also requires a one-time inspection to determine if a tool runout option has been performed in the area. That AD resulted from a report indicating that, during a routine maintenance inspection, fractured lugs were found on both hinge fittings of the outboard hinge assembly mounted to the inboard main flap on a Boeing Model 767-300 series airplane. We issued that AD to prevent the inboard aft flap from separating from the wing and potentially striking the airplane, which could result in damage to the surrounding structure and potential personal injury.
Since we issued AD 2003-13-01, Amendment 39-13201 (68 FR 37402, June 24, 2003), we have determined that, due to hinge assembly fractures found before the currently-required inspection cycle compliance times on certain airplanes affected by that AD, compliance times need to be reduced for the initial and repetitive inspections for Model 767-400ER series airplanes.
In addition, we have determined that the airplane having line number 877 was inadvertently omitted from the applicability of AD 2003-13-01, Amendment 39-13201 (68 FR 37402, June 24, 2003).
AD 2003-13-01, Amendment 39-13201 (68 FR 37402, June 24, 2003), referred to Boeing Alert Service Bulletin 767-57A0079, dated June 20, 2002, as the appropriate source of service information for inspections and terminating actions for Model 767-400ER series airplanes. Boeing has since revised this service bulletin. We reviewed Boeing Alert Service Bulletin 767-57A0079, Revision 1, dated May 6, 2010. This service bulletin reduces the initial compliance time and repetitive intervals for inspections of the outboard hinge fitting assemblies on the trailing edge of the inboard main flap for Model 767-400ER series airplanes.
This proposed AD would retain certain requirements of AD 2003-13-01, Amendment 39-13201 (68 FR 37402, June 24, 2003). This proposed AD would reduce the compliance times for Model 767-400ER series airplanes. In addition, this proposed AD would revise the applicability to include an additional airplane.
This proposed AD would retain certain requirements of AD 2003-13-01, Amendment 39-13201 (68 FR 37402, June 24, 2003). Since AD 2003-13-01 was issued, the AD format has been revised, and certain paragraphs have been rearranged. As a result, the corresponding paragraph identifiers have changed in this proposed AD, as listed in the following table:
Requirement in AD 2003-13-01 Amendment 39-13201 (68 FR 37402, June 24, 2003)
paragraph (c) paragraph (i)(1)
paragraph (d) paragraph (i)(2)
paragraph (f) paragraph (j)
paragraph (g) paragraph (l)
paragraph (h) paragraph (k)
Because there is no longer a need for inspection results, this proposed AD would also remove the reporting requirement from AD 2003-13-01, Amendment 39-13201 (68 FR 37402, June 24, 2003).
We estimate that this proposed AD affects 38 airplanes of U.S. registry.
Detailed inspection [retained from AD 2003-13-01, Amendment 39-13201 (68 FR 37402, June 24, 2003)] 2 work-hours × $85 per hour = $170 per inspection cycle $0 $170 per inspection cycle $6,460 per inspection cycle.
Detailed and eddy current inspections [retained from AD 2003-13-01, Amendment 39-13201 (68 FR 37402, June 24, 2003)] 5 work hours × $85 per hour = $425 per inspection cycle 0 $425 per inspection cycle $16,150 per inspection cycle.
Replacement [retained from AD 2003-13-01, Amendment 39-13201 (68 FR 37402, June 24, 2003)] 24 work hours × $85 per hour = $2,040 $45,400 $47,440
2. The FAA amends § 39.13 by removing airworthiness directive (AD) 2003-13-01, Amendment 39-13201 (68 FR 37402, June 24, 2003), and adding the following new AD:
The Boeing Company: Docket No. FAA-2012-0108; Directorate Identifier 2011-NM-049-AD.
The FAA must receive comments on this AD action by March 26, 2012.
This AD supersedes AD 2003-13-01, Amendment 39-13201 (68 FR 37402, June 24, 2003).
The Boeing Company Model 767-200, -300, and -300F series airplanes, as specified in Boeing Service Bulletin 767-57A0076, Revision 1, dated March 29, 2001; and Model 767-400ER series airplanes, as specified in Boeing Alert Service Bulletin 767-57A0079, Revision 1, dated May 6, 2010; certificated in any category.
This AD was prompted by reports of hinge assembly fractures found before the currently-required inspection cycle compliance times on certain airplanes. We are issuing this AD to prevent the inboard aft flap from separating from the wing and potentially striking the airplane, which could result in damage to the surrounding structure and potential personal injury.
Perform either a detailed inspection, or a detailed inspection plus an eddy current inspection, of the outboard hinge fitting assemblies on the trailing edge of the inboard main flap to detect cracks and fractures and evidence of a tool runout option, as applicable. For the purposes of this AD, a detailed inspection is defined as: “An intensive visual examination of a specific structural area, system, installation, or assembly to detect damage, failure, or irregularity. Available lighting is normally supplemented with a direct source of good lighting at intensity deemed appropriate by the inspector. Inspection aids such as mirror, magnifying lenses, etc., may be used. Surface cleaning and elaborate access procedures may be required.”
(1) For Model 767-200, -300, and -300F series airplanes identified in Boeing Service Bulletin 767-57A0076, Revision 1, dated March 29, 2001: Inspect before the airplane accumulates 2,700 total flight cycles, or within 90 days after July 29, 2003 (the effective date of AD 2003-13-01, Amendment 39-13201 (68 FR 37402, June 24, 2003)), whichever occurs later, in accordance with Boeing Service Bulletin 767-57A0076, Revision 1, dated March 29, 2001.
(2) For Model 767-400ER series airplanes identified in Boeing Alert Service Bulletin 767-57A0079, dated June 20, 2002: Inspect before the airplane accumulates 12,000 total flight cycles, except as required by paragraph (m) of this AD, in accordance with Boeing Alert Service Bulletin 767-57A0079, dated June 20, 2002; or Revision 1, dated May 6, 2010. As of the effective date of this AD, only Revision 1 may be used.
Following the initial inspections required by paragraph (g) of this AD: Perform applicable follow-on and corrective actions at the times specified in Figure 1 of Boeing Service Bulletin 767-57A0076, Revision 1, dated March 29, 2001 (for Model 767-200, -300, and -300F series airplanes); or Boeing Alert Service Bulletin 767-57A0079, dated June 20, 2002, or Boeing Alert Service Bulletin 767-57A0079, Revision 1, dated May 6, 2010 (for Model 767-400ER series airplanes); until the inspection required by paragraph (n) of this AD is accomplished. After the effective date of this AD, only Boeing Alert Service Bulletin 767-57A0079, Revision 1, dated May 6, 2010, may be used for Model 767-400ER series airplanes. Do the follow-on and corrective actions (including repetitive inspections and replacement of the fittings with new fittings), in accordance with Part 1 or Part 2 of Boeing Service Bulletin 767-57A0076, Revision 1, dated March 29, 2001 (for Model 767-200, -300, and -300F series airplanes); or Boeing Alert Service Bulletin 767-57A0079, dated June 20, 2002, or Boeing Alert Service Bulletin 767-57A0079, Revision 1, dated May 6, 2010 (for Model 767-400ER series airplanes); except as required by paragraph (i)(2) of this AD. After the effective date of this AD, only Boeing Alert Service Bulletin 767-57A0079, Revision 1, dated May 6, 2010, may be used for Model 767-400ER series airplanes. For Model 767-200, -300, and -300F series airplanes: If the fitting has the tool runout, and no cracking or fracture is found during the inspection, this AD requires no further action for that hinge fitting.
For this AD, the following exceptions apply:
(1) Where the terminating action in Part 3 of Boeing Service Bulletin 767-57A0076, Revision 1, dated March 29, 2001; and Boeing Alert Service Bulletin 767-57A0079, dated June 20, 2002, and Revision 1, dated May 6, 2010; is specified as corrective action: This AD requires that the terminating action, if required, be accomplished before further flight.
(2) Boeing Service Bulletin 767-57A0076, Revision 1, dated March 29, 2001, specifies to contact Boeing before the terminating action is done as corrective action for any cracking or fracture found on a Model 767-200, -300, or -300F series airplane with the tool runout. This AD requires that any such crack or fracture on those airplanes be repaired in accordance with Part 3 of Boeing Service Bulletin 767-57A0076, Revision 1, dated March 29, 2001. This AD does not require a report.
Unless required to do so by paragraph (h) of this AD: Operators may choose to accomplish the terminating action (including replacement of the fittings with new fittings, and reinstallation of existing upper skin access panels and fairing midsections on the trailing edge of the main flap) in accordance with Part 3 of the Work Instructions of Boeing Service Bulletin 767-57A0076, Revision 1, dated March 29, 2001; or Boeing Alert Service Bulletin 767-57A0079, dated June 20, 2002, or Boeing Alert Service Bulletin 767-57A0079, Revision 1, dated May 6, 2010; as applicable. After the effective date of this AD, only Boeing Alert Service Bulletin 767-57A0079, Revision 1, dated May 6, 2010, may be used for Model 767-400ER series airplanes. Accomplishment of the terminating action terminates the repetitive inspection requirements of paragraph (h) of this AD.
As of July 29, 2003, no person may install on any airplane identified in Boeing Service Bulletin 767-57A0076, dated October 26, 2000; and Boeing Alert Service Bulletin 767-57A0079, dated June 20, 2002; a hinge fitting assembly that has any part number listed in table 1 of this AD, unless the applicable requirements of this AD have been accomplished for that fitting. As of the effective date of this AD, no person may install on any airplane identified in paragraph (c) of this AD, a hinge fitting assembly that has any part number listed in table 1 of this AD, unless the applicable requirements of this AD have been accomplished for that fitting.
Table 1—Hinge Fitting Assembly Part Numbers
113T2271-13 113T2271-14
113T2271-23 113T2271-24
113T2271-29 113T2271-30
113T2271-33 113T2271-34
113T2271-401 113T2271-402
Actions done before July 29, 2003, in accordance with Boeing Alert Service Bulletin 767-57A0076, dated October 26, 2000, are acceptable for compliance with the corresponding requirements of paragraphs (g), (h), (j), and (k) of this AD.
For Model 767-400ER airplanes identified in Boeing Alert Service Bulletin 767-57A0079, Revision 1, dated May 6, 2010, on which the inspection required in paragraph (g) of this AD has not been done as of the effective date of this AD: Before the accumulation of 6,000 total flight cycles, or within 750 flight cycles after the effective date of this AD, whichever occurs later, perform either a detailed inspection or a detailed inspection plus an eddy current inspection to detect cracks or fractures of the outboard hinge fitting assemblies on the trailing edge of the inboard main flap, in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 767-57A0079, Revision 1, dated May 6, 2010. Accomplishment of this inspection terminates the inspection requirement of paragraph (g)(2) of this AD.
For Model 767-400ER airplanes: Repeat either inspection specified in paragraph (h) or (m) of this AD, as applicable, at the time specified in paragraph (n)(1) or (n)(2) of this AD, as applicable, in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 767-57A0079, Revision 1, dated May 6, 2010.
(1) If the most recent inspection was a detailed inspection, repeat at intervals not to exceed 300 flight cycles after doing the detailed inspection.
(2) If the most recent inspections were a detailed inspection and an eddy current inspection, repeat at intervals not to exceed 750 flight cycles after doing the detailed inspection and eddy current inspection.
For Model 767-400ER airplanes: Replacing the fittings with new fittings, in accordance with Part 3 of the Work Instructions of Boeing Alert Service Bulletin 767-57A0079, dated June 20, 2002; or Revision 1, dated May 6, 2010; terminates the repetitive inspections required by paragraphs (h) and (n) of this AD.
Actions done before the effective date of this AD in accordance with Part 3 of the Work Instructions of Boeing Alert Service Bulletin 767-57A0079, dated June 20, 2002, are acceptable for compliance with the requirements of paragraph (h) and (n) of this AD.
(1) For more information about this AD, contact Berhane Alazar, Aerospace Engineer, Airframe Branch, ANM-120S, FAA, Seattle Aircraft Certification Office, 1601 Lind Avenue SW., Renton, Washington 98057-3356; phone: 425-917-6577; fax: 425-917-6590; email: berhane.alazar@faa.gov.
(2) For service information identified in this AD, contact Boeing Commercial Airplanes, Attention: Data & Services Management, P.O. Box 3707, MC 2H-65, Seattle, Washington 98124-2207; telephone 206-544-5000, extension 1; fax 206-766-5680; email me.boecom@boeing.com; Internet https://www.myboeingfleet.com. You may review copies of the referenced service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, Washington. For information on the availability of this material at the FAA, call 425-227-1221.
Issued in Renton, Washington, on January 27, 2012.
[FR Doc. 2012-2976 Filed 2-8-12; 8:45 am]