Source: https://www.federalregister.gov/documents/2013/10/02/2013-24040/airworthiness-directives-the-boeing-company-airplanes
Timestamp: 2018-04-26 16:02:11
Document Index: 699372998

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

78 FR 60804
60804-60807 (4 pages)
Docket No. FAA-2013-0836
Directorate Identifier 2013-NM-126-AD
2013-24040
Actions Since AD 2005-07-12, Amendment 39-14036 (70 FR 17596, April 7, 2005) Was Issued
(g) Group 1 Airplanes: Inspections and Corrective Actions
(h) Group 2 and Group 3 Airplanes: Inspections and Corrective Actions
https://www.federalregister.gov/d/2013-24040 https://www.federalregister.gov/d/2013-24040
We propose to supersede airworthiness directive (AD) 2005-07-12 that applies to certain The Boeing Company Model 737-100, -200, -200C, -300, -400, and -500 series airplanes. AD 2005-07-12 requires detailed and eddy current inspections to detect cracking of the frame web around the cutout for the doorstop intercostal strap at the aft side of the station (STA) 291.5 frame at stringer 16R, and corrective action if necessary. Since we issued AD 2005-07-12, we received reports of new findings of cracking at various locations of the STA 277 to STA 291.5 frames and intercostals, including webs, chords, clips, and shear ties, between stringers 7R and 17R. This proposed AD would add new inspections for cracking at the forward galley door cutout, and corrective actions if necessary. This proposed AD would also reduce a certain inspection threshold required by AD 2005-07-12. We are proposing this AD to detect and correct fatigue cracking of the aft frame and frame support structure of the forward galley door, which could result in a severed fuselage frame web, rapid decompression of the airplane, and possible loss of the forward galley door.
You may send comments, using the procedures found in 14 CFR 11.43 and 11.45, by any of the following methods:Start Printed Page 60805
For service information identified in this AD, contact Boeing Commercial Airplanes, Attention: Data & Services Management, P.O. Box 3707, MC 2H-65, Seattle, WA 98124-2207; telephone 206-544-5000, extension 1; fax 206-766-5680; Internet https://www.myboeingfleet.com. You may review copies of the referenced service information at the FAA, Transport Airplane Directorate, 1601 Lind Ave. SW., Renton, Washington. For information on the availability of this material at the FAA, call 425-227-1221.
Alan Pohl, Aerospace Engineer, Airframe Branch, ANM-120S, FAA Seattle Aircraft Certification Office, 1601 Lind Avenue SW., Renton, Washington 98057-3356; phone: 425-917-6450; fax: 425-917-6590; email: alan.pohl@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-2013-0836; Directorate Identifier 2013-NM-126-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 March 25, 2005, we issued AD 2005-07-12, Amendment 39-14036 (70 FR 17596, April 7, 2005), for certain The Boeing Company Model 737-100, -200, -300, -400, and -500 series airplanes. AD 2005-07-12 requires repetitive detailed and eddy current inspections to detect cracking of the frame web around the cutout for the doorstop intercostal strap at the aft side of STA 291.5 frame at stringer 16R, and corrective actions if necessary. We issued AD 2005-07-12 to detect and correct fatigue cracking of the aft frame and frame support structure of the forward galley door.
Since we issued AD 2005-07-12, Amendment 39-14036 (70 FR 17596, April 7, 2005) Boeing has received 24 reports of cracking of the STA 291.5 frame web around the doorstop intercostal strap cutout at stringer 16R. There have been 23 reports of cracks propagating down from the lower radius of the cutout on airplanes that had accumulated between 35,597 and 68,133 total flight cycles. Boeing also received one report of a crack propagating outboard from the upper radius through two countersunk fastener locations on an airplane that had accumulated 31,611 total flight cycles. In addition, Boeing received reports of cracking in other areas of the forward galley door cutout that are determined to be safety related.
We reviewed Boeing Alert Service Bulletin 737-53A1241, Revision 1, dated June 11, 2013. For information on the procedures and compliance times, see this service information at http://www.regulations.gov by searching for Docket No. FAA-2013-0836.
Although this proposed AD does not explicitly restate the requirements of AD 2005-07-12, Amendment 39-14036 (70 FR 17596, April 7, 2005) this proposed AD would retain all of the requirements of AD 2005-07-12. Those requirements are referenced in the service information identified previously, which, in turn, is referenced in paragraph (h) of this proposed AD. For certain airplanes, this proposed AD would reduce the compliance threshold for a certain inspection. This proposed AD would also require accomplishing the actions identified in the service information identified previously, except as discussed under “Differences Between the Proposed AD and the Service Information.”
Boeing Alert Service Bulletin 737-53A1241, Revision 1, dated June 11, 2013, specifies to contact the manufacturer for instructions on how to repair certain conditions, but this proposed AD would require repairing those conditions in one of the following ways:
We estimate the following costs to comply with this proposed AD:Start Printed Page 60806
Inspections [retained from AD 2005-07-12, Amendment 39-14036 (70 FR 17596)] 2 work-hours × $85 per hour = $170 per inspection cycle None $170 per inspection cycle $71,230 per inspection cycle.
Inspections [new proposed action] 40 work-hours × $85 per hour = $3,400 per inspection cycle None $3,400 per inspection cycle $1,424,600 per inspection cycle.
We have received no definitive data that would enable us to provide a cost estimate for the on-condition actions specified in the service information.
2. The FAA amends § 39.13 by removing airworthiness directive (AD) 2005-07-12, Amendment 39-14036 (
The Boeing Company: Docket No. FAA-2013-0836; Directorate Identifier 2013-NM-126-AD.
The FAA must receive comments on this AD action by November 18, 2013.
This AD supersedes AD 2005-07-12, Amendment 39-14036 (70 FR 17596, April 7, 2005).
This AD applies to The Boeing Company Model 737-100, -200, -200C, -300, -400, and -500 series airplanes, as identified in Boeing Alert Service Bulletin 737-53A1241, Revision 1, dated June 11, 2013.
This AD was prompted by reports of new findings of cracking at various locations of the stations (STA) 277 to STA 291.5 frames and intercostals, including webs, chords, clips, and shear ties, between stringers 7R and 17R. We are issuing this AD to detect and correct fatigue cracking of the aft frame and frame support structure of the forward galley door, which could result in a severed fuselage frame web, rapid decompression of the airplane, and possible loss of the forward galley door.
For airplanes identified as Group 1 in Boeing Alert Service Bulletin 737-53A1241, Revision 1, dated June 11, 2013: Within 120 days after the effective date of this AD, do inspections for cracking from STA 277 to STA 328, stringer 7R to 17R of the forward galley door cutout, using a method approved in accordance with the procedures specified in paragraph (l) of this AD. Do all applicable corrective actions before further flight using a method approved in accordance with the procedures specified in paragraph (l) of this AD.
(1) For airplanes identified as Group 2 and Group 3 in Boeing Alert Service Bulletin 737-53A1241, Revision 1, dated June 11, 2013: Except as provided by paragraph (j)(2) of this AD, at the applicable times specified in tables 1 and 2 in paragraph 1.E, “Compliance,” of Boeing Alert Service Bulletin 737-53A1241, Revision 1, dated June 11, 2013, do detailed and surface HFEC inspections, as applicable, for cracking in the forward galley door cutout, in accordance with Part 2 of the Accomplishment Instructions of Boeing Alert Service Bulletin 737-53A1241, Revision 1, dated June 11, 2013. Repeat the detailed and surface HFEC inspections thereafter at the applicable intervals specified in tables 1 and 2 in paragraph 1.E, “Compliance,” of Boeing Alert Service Bulletin 737-53A1241, Revision 1, dated June 11, 2013. If any crack is found, before further flight, do all applicable corrective actions in accordance with Part 2 of the Accomplishment Instructions of Boeing Alert Service Bulletin 737-53A1241, Revision 1, dated June 11, 2013, except as required by paragraph (j)(1) of this AD. Doing the repair in accordance with Part 2 of the Accomplishment Instructions of Boeing Alert Service Bulletin 737-53A1241, Revision 1, dated June 11, 2013, terminates the repetitive inspections required by this paragraph for the repaired area only.
(2) Removal and replacement of a cracked part, in accordance with Part 2 of the Accomplishment Instructions of Boeing Alert Service Bulletin 737-53A1241, Revision 1, dated June 11, 2013, does not terminate the Start Printed Page 60807repetitive inspections required by paragraph (h)(1) of this AD.
Accomplishment of the preventive modification on the STA 291.5 frame web, in accordance with Part 2 of the Accomplishment Instructions of Boeing Alert Service Bulletin 737-53A1241, Revision 1, dated June 11, 2013, terminates the repetitive inspections required by paragraph (h)(1) of this AD for the area that is common to the preventive modification.
(1) Where Boeing Alert Service Bulletin 737-53A1241, Revision 1, dated June 11, 2013, specifies to contact Boeing for a corrective action: Before further flight, do the applicable action using a method approved in accordance with the procedures specified in paragraph (l) of this AD.
(2) Where paragraph 1.E., “Compliance,” of Boeing Alert Service Bulletin 737-53A1241, Revision 1, dated June 11, 2013, specifies a compliance time “after the date on Revision 1 of this service bulletin,” this AD requires compliance within the specified compliance time after the effective date of this AD.
This paragraph provides credit for the actions specified in paragraph (h)(1) of this AD, if those actions were performed before the effective date of this AD using Boeing Alert Service Bulletin 737-53A1241, dated June 13, 2002, which is not incorporated by reference in this AD.
(4) AMOCs approved for the actions specified in AD 2005-07-12, Amendment 39-14036 (70 FR 17596, April 7, 2005), are approved as AMOCs for the corresponding provisions of this AD.
(1) For more information about this AD, contact Alan Pohl, Aerospace Engineer, Airframe Branch, ANM-120S, FAA Seattle Aircraft Certification Office, 1601 Lind Avenue SW., Renton, Washington 98057-3356; phone: 425-917-6450; fax: 425-917-6590; email: alan.pohl@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, WA 98124-2207; telephone 206-544-5000, extension 1; fax 206-766-5680; Internet https://www.myboeingfleet.com. You may review copies of the referenced service information at the FAA, Transport Airplane Directorate, 1601 Lind Ave. SW., Renton, Washington. For information on the availability of this material at the FAA, call 425-227-1221.
Issued in Renton, Washington on September 25, 2013.
[FR Doc. 2013-24040 Filed 10-1-13; 8:45 am]