Source: https://www.federalregister.gov/documents/2013/08/06/2013-18765/airworthiness-directives-the-boeing-company-airplanes
Timestamp: 2017-08-21 20:34:52
Document Index: 461315090

Matched Legal Cases: ['art 39', 'art 2', 'arts 1', 'arts 5', 'art 5', 'art 6', 'arts 1', 'arts 5', 'arts 1', '§\u200939', 'art 1', 'arts 1', 'arts 5', 'art 17', 'art 11']

78 FR 47549
47549-47555 (7 pages)
Amendment 39-17500
AD 2013-13-12
2013-18765
Request To Revise Requirement To Determine Door Configuration
Request To Clarify Access Procedures
Request To Clarify Required Part References for Compliance
Request To Exclude Certain Supplemental Structural Inspections
Request To Delay Final Rule Pending Revised Service Information
https://www.federalregister.gov/d/2013-18765 https://www.federalregister.gov/d/2013-18765
We are superseding airworthiness directive (AD) 2000-06-13 R1, which applied to certain The Boeing Company Model 737-200, -200C, -300, and -400 series airplanes. AD 2000-06-13 R1 required repetitively inspecting for cracking of the corners of the door frame and the cross beams of the aft cargo door, and corrective actions if necessary. AD 2000-06-13 R1 also required modifying the aft cargo door, which terminates the repetitive inspections. This new AD adds airplanes to the applicability, adds inspections and related investigative and corrective actions, revises certain inspection types, and reduces a certain compliance time for modifying the doors. This AD was prompted by reports of cracking in the forward and aft corner frames of the aft cargo door and in the lower cross beam. We are issuing this AD to prevent fatigue cracking of the corners of the door frame and the cross beams of the aft cargo door, which could result in rapid depressurization of the airplane.
The Director of the Federal Register approved the incorporation by reference of certain publications listed in the AD as of September 10, 2013.
The Director of the Federal Register approved the incorporation by reference of a certain other publication listed in this AD as of May 9, 2000 (65 FR 17583, April 4, 2000).
The Director of the Federal Register approved the incorporation by reference of a certain other publication listed in this AD as of December 24, 1998 (63 FR 67769, December 9, 1998).
Alan Pohl, Aerospace Engineer, Airframe Branch, ANM-120S, FAA, Seattle Aircraft Certification Office, 1601 Lind Avenue SW., Renton, Start Printed Page 47550Washington 98057-3356; phone: 425-917-6450; fax: 425-917-6590; email: alan.pohl@faa.gov.
We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 to supersede AD 2000-06-13 R1, Amendment 39-12317 (66 FR 36146, July 11, 2001), which revised AD 2000-06-13, Amendment 39-11654 (65 FR 17583, April 4, 2000). AD 2000-06-13 superseded AD 98-25-06, Amendment 39-10931 (63 FR 67769, December 9, 1998). AD 2000-06-13 R1 applied to the specified products. The NPRM published in the Federal Register on December 4, 2012 (77 FR 71723). The NPRM proposed to continue to require repetitively inspecting for cracking of the corners of the door frame and the cross beams of the aft cargo door; doing corrective actions if necessary; and modifying the aft cargo door, which terminates the repetitive inspections. The NPRM also proposed to add airplanes to the applicability, add inspections and related investigative and corrective actions, revise certain inspection types, and reduce a certain compliance time for modifying the doors.
We gave the public the opportunity to participate in developing this AD. The following presents the comments received on the proposal (77 FR 71723, December 4, 2012) and the FAA's response to each comment.
Boeing requested that we revise paragraph (o) of the NPRM (77 FR 71723, December 4, 2012), which specified the compliance time by referring to paragraph 1.E. of Boeing Alert Service Bulletin 737-52A1153, dated July 13, 2011. Boeing requested that we change this compliance time to “4,500 door flight cycles after the effective date of this AD” to avoid a potential conflict with other compliance times in the NPRM. Boeing explained a scenario in which an operator could comply with paragraph (o) of the NPRM within the required compliance time, but then be immediately out of compliance with the proposed inspection in paragraphs (p) and (q) of the NPRM.
We partially agree with the request. As written, the compliance time in paragraph (o) of the NPRM (77 FR 71723, December 4, 2012) could result in a compliance conflict with other requirements of this AD for doors subject to Boeing Alert Service Bulletin 737-52A1079, Revision 7, dated December 17, 2010. We disagree, however, with Boeing's requested compliance time, which would be unnecessarily more restrictive on operators. Also, the referenced doors that have accumulated fewer than 27,000 total flight cycles should be provided the same compliance time as doors subject to Boeing Alert Service Bulletin 737-52A1153, dated July 13, 2011. We have therefore revised paragraphs (p) and (q) in this final rule to change the compliance time to a threshold of 27,000 total flight cycles on the door, with a grace period of 4,500 flight cycles. Since paragraph (u)(4) of the NPRM is therefore no longer necessary, we have removed that paragraph from this final rule.
Southwest Airlines (SWA) requested that we revise paragraph (o) of the NPRM (77 FR 71723, December 4, 2012), which specified to “Inspect the door to determine the configuration, in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 737-52A1153, dated July 13, 2011.” SWA considered that the intent of this proposed requirement could be accomplished by records research instead of a physical inspection. The commenter noted that the Accomplishment Instructions of this service bulletin specify only identifying the part number of the aft cargo door assembly, and does not specify a method of accomplishment.
We agree with the commenter that a records review is acceptable in lieu of accomplishing an inspection to determine the configuration of the door. We have changed paragraph (o) accordingly in this final rule.
All Nippon Airways (ANA) and Boeing requested that we revise the NPRM (77 FR 71723, December 4, 2012) to also refer to Boeing Special Attention Service Bulletin 737-52-1154, Revision 1, dated August 3, 2011, in all locations where Boeing Service Bulletin 737-52-1154, dated December 17, 2010, is cited. The commenters noted that some locations of the NPRM referred to only the original version, but other paragraphs referred to the original version “as revised by Boeing Special Attention Service Bulletin 737-52-1154, Revision 1, dated August 3, 2011.”
We agree with the commenter and have revised paragraphs (r)(2) and (u)(2) in this final rule to also add “as revised by Boeing Special Attention Service Bulletin 737-52-1154, Revision 1, dated August 3, 2011,” after the original service bulletin citation.
ANA noted that paragraph (s) of the NPRM (77 FR 71723, December 4, 2012) identified certain Parts in the Accomplishment Instructions of Boeing Alert Service Bulletin 737-52A1153, dated July 13, 2011, for compliance with the proposed requirements. ANA stated that Part 2, which was not identified in paragraph (s) of the NPRM, provides access procedures. ANA questioned whether the AD required specific procedures for access.
We agree, and have added new paragraph (u)(4) in this final rule to clarify that the access and restoration procedures specified in the referenced service information are not required by this AD.
ANA noted that paragraph (t) of the NPRM (77 FR 71723, December 4, 2012) referred to Parts 1, 3, 4, 7, and 8 of the Accomplishment Instructions of Boeing Alert Service Bulletin 737-52A1153, dated July 13, 2011. Table 3 and Table 4 of that service bulletin also refer to Parts 5 and 6 of that service bulletin. ANA questioned whether operators might do Part 5 and Part 6, which describe the preventive modification procedures, if no cracks are found. To avoid the need for requests for alternative methods of compliance (AMOCs) regarding this proposed requirement, ANA requested that we revise paragraph (t) of the NPRM to clarify that compliance is “in accordance with Parts 1, 2, 3, 4, 5, 6, 7, and 8” of that service bulletin.
We disagree with the commenter. Paragraph (s) requires actions in accordance with Parts 5 and 6 of the Accomplishment Instructions of Boeing Alert Service Bulletin 737-52A1153, dated July 13, 2011. Paragraph (t) of this AD requires other actions, done in accordance with Parts 1, 3, 4, 7, and 8 of that service bulletin. We find it unnecessary to change this AD regarding this issue.
Paragraph (v) of the NPRM (77 FR 71723, December 4, 2012) would provide relief from certain supplemental structural inspections specified in Boeing Alert Service Bulletin 737-52A1153, dated July 13, 2011, and Boeing Alert Service Bulletin 737-52A1079, Revision 7, dated December Start Printed Page 4755117, 2010. Boeing requested that we revise paragraph (v) of the NPRM to also provide relief from the supplemental structural inspections specified in Table 5 of paragraph 1.E., “Compliance,” of Boeing Service Bulletin 737-52-1154, dated December 17, 2010. Boeing noted that the NPRM would require inspection of the adjacent cross beam if cracks are found in the lower cross beam, and repair of any cracked adjacent cross beam, in accordance with Boeing Service Bulletin 737-52-1154, dated December 17, 2010, but the damage-tolerance inspections associated with that repair are not mentioned.
We agree with the request. We have revised paragraph (v) in this final rule to also include reference to Table 5 of Boeing Service Bulletin 737-52-1154, dated December 17, 2010.
ANA stated that Boeing was in the process of revising Boeing Service Bulletins 737-52-1153 and 737-52-1154 based on ANA's validation. ANA requested that we cite the revised service information, if it is available before the final rule is issued, to reduce additional burden for Boeing and the operators. Boeing reported that Boeing Service Bulletin 737-52-1154 was being revised to add extra material to the repair parts to address issues regarding repair kits found during the validation of the bulletin.
We disagree to delay issuance of the final rule pending issuance of revised service information. Accomplishing the service information specified in this AD addresses the identified unsafe condition. When the revised service bulletins are presented to us for review, however, we might consider approving them as AMOCs for this AD. We have not changed this final rule regarding this issue.
We have revised paragraph (v) and Note 2 to paragraph (v) of this final rule. We have designated paragraph (v) as paragraph (v)(1) of this final rule, and have reidentified Note 2 to paragraph (v) as paragraph (v)(2) of this final rule.
Are consistent with the intent that was proposed in the NPRM (77 FR 71723, December 4, 2012) for correcting the unsafe condition; and
Do not add any additional burden upon the public than was already proposed in the NPRM (77 FR 71723, December 4, 2012).
We estimate that this AD affects 581 airplanes of U.S. registry. We estimate the following costs to comply with this AD:
Detailed inspection (retained action) 2 work-hours × $85 per hour = $170 per inspection cycle $0 $170 per inspection cycle 494 $83,890 per inspection cycle.
High frequency eddy current inspection (retained action) 4 work-hours × $85 per hour = $340 per inspection cycle 0 $340 per inspection cycle 494 $167,960 per inspection cycle.
Modification (retained action) 144 work-hours × $85 per hour = $12,240 5,430 $17,670 494 $8,728,980.
Determination of door configuration (new action) 1 work-hour × $85 per hour = $85 0 $85 581 $49,385.
Inspections (new action) 6 work-hours × $85 per hour = $510 per inspection cycle 0 $510 per inspection cycle 581 $296,310 per inspection cycle.
Modification (new action) 59 work-hours × $85 per hour = $5,015 30,536 $35,551 * Unknown.
* The number of airplanes that require this modification depends on no cracking being found during a certain inspection.
We estimate the following costs to do any necessary related investigative and corrective actions that would be required based on the results of the inspections. We have no way of determining the number of aircraft that might need these actions:
We are issuing this rulemaking under the authority described in Subtitle VII, Start Printed Page 47552Part A, Subpart III, Section 44701, “General requirements.” Under that section, Congress charges the FAA with promoting safe flight of civil aircraft in air commerce by prescribing regulations for practices, methods, and procedures the Administrator finds necessary for safety in air commerce. This regulation is within the scope of that authority because it addresses an unsafe condition that is likely to exist or develop on products identified in this rulemaking action.
2. The FAA amends § 39.13 by removing airworthiness directive (AD) 2000-06-13 R1, Amendment 39-12317 (
2013-13-12 The Boeing Company: Amendment 39-17500 ; Docket No. FAA-2012-1156; Directorate Identifier 2011-NM-205-AD.
This AD supersedes AD 2000-06-13 R1, Amendment 39-12317 (66 FR 36146, July 11, 2001).
(4) If any cracking is detected in the forward or aft lower door frame, prior to further flight, replace the damaged frame with a new frame, and modify the corners of the door frame of the aft cargo door, in accordance with Part I of the Accomplishment Instructions of Boeing Service Bulletin 737-52-1079, Revision 5, dated May 16, 1996; Part I of the Accomplishment Instructions of Boeing Alert Service Bulletin 737-52A1079, Revision 6, dated November 18, 1999; or Part II of the Accomplishment Instructions of Boeing Alert Service Bulletin 737-52A1079, Revision 7, dated December 17, 2010. Accomplishment of such modification constitutes terminating Start Printed Page 47553action for the repetitive inspection requirements of paragraph (h)(1)(i) of this AD for the lower door frame.
At the applicable time specified in Table 1 of paragraph 1.E., “Compliance,” of Boeing Alert Service Bulletin 737-52A1153, dated July 13, 2011, except as provided by paragraph (u)(1) of this AD: Inspect to determine the configuration of the aft cargo door, in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 737-52A1153, dated July 13, 2011. A review of airplane maintenance records is acceptable in lieu of this inspection if the configuration of the cargo door can be conclusively determined from that review.
If, during the inspection required by paragraph (o) of this AD, any door is determined to be from any airplane having line numbers 6 through 873 inclusive, and neither the modification nor the repair specified in any service bulletin identified in paragraphs (p)(1) through (p)(7) of this AD has been done as of the effective date of this AD: Do a one-time HFEC and a one-time ultrasonic inspection for cracking of the upper and lower corner frames and the upper and lower cross beams, and do all applicable related investigative and corrective actions, in accordance with Parts II, III, IV, and VI of the Accomplishment Instructions of Boeing Alert Service Bulletin 737-52A1079, Revision 7, dated December 17, 2010; and, as applicable, the Accomplishment Instructions of Boeing Special Attention Service Bulletin 737-52-1154, dated December 17, 2010, as revised by Boeing Special Attention Service Bulletin 737-52-1154, Revision 1, dated August 3, 2011; except as provided by paragraphs (u)(2) and (u)(3) of this AD. Do the inspections before the accumulation of 27,000 total flight cycles on the door, or within 4,500 door flight cycles after the Start Printed Page 47554effective date of this AD, whichever occurs later (for airplanes on which the door flight cycles are known); or within 4,500 flight cycles after the effective date of this AD (for airplanes on which door flight cycles are not known). Do all applicable related investigative and corrective actions before further flight. If no cracking is found during the initial inspections, before further flight, do the modification in accordance with Part III of the Accomplishment Instructions of Boeing Alert Service Bulletin 737-52A1079, Revision 7, dated December 17, 2010. Doing the inspection specified in this paragraph terminates the inspections required by paragraphs (h) and (k) of this AD.
If, during the inspection required by paragraph (o) of this AD, any door is determined to be from any airplane having line numbers 6 through 873 inclusive: Before the accumulation of 27,000 total flight cycles on the door, or within 4,500 door flight cycles after the effective date of this AD, whichever occurs later, (for airplanes on which the door flight cycles are known); or within 4,500 flight cycles after the effective date of this AD (for airplanes on which door flight cycles are not known); inspect the lower corner frames to determine if the door has reinforcement angles, P/N 65C25180-9, -43, -10, -11, or -12, that were installed as specified in any service bulletin identified in paragraphs (q)(1) through (q)(5) of this AD. If any affected reinforcement angle is found, do a one-time general visual inspection for edge margin and do a detailed inspection for cracks; in accordance with Part V of the Accomplishment Instructions of Boeing Alert Service Bulletin 737-52A1079, Revision 7, dated December 17, 2010.
(2) Do a one-time detailed inspection or HFEC inspection for cracking at the forward and aft ends of cross beam D, in accordance with Part 1 of the Accomplishment Instructions of Boeing Special Attention Service Bulletin 737-52-1154, dated December 17, 2010; or Boeing Special Attention Service Bulletin 737-52-1154, dated December 17, 2010, as revised by Boeing Special Attention Service Bulletin 737-52-1154, Revision 1, dated August 3, 2011. If any cracking is found, before further flight, do all applicable repairs in accordance with the Accomplishment Instructions of Boeing Special Attention Service Bulletin 737-52-1154, dated December 17, 2010; or Boeing Special Attention Service Bulletin 737-52-1154, dated December 17, 2010, as revised by Boeing Special Attention Service Bulletin 737-52-1154, Revision 1, dated August 3, 2011, except as provided by paragraph (u)(2) of this AD.
If, during the action required by paragraph (o) of this AD, a door is determined to be from an airplane having line numbers 874 and subsequent: At the applicable time specified in Tables 1 and 2 of paragraph 1.E., “Compliance,” of Boeing Alert Service Bulletin 737-52A1153, dated July 13, 2011, except as provided by paragraph (u)(1) of this AD, do high frequency and detailed inspections for cracks in the forward and aft ends of cross beam E, and do all applicable related investigative and corrective actions, in accordance with Parts 1, 3, 4, 5, and 6 of the Accomplishment Instructions of Boeing Alert Service Bulletin 737-52A1153, dated July 13, 2011; and, as applicable, the Accomplishment Instructions of Boeing Special Attention Service Bulletin 737-52-1154, dated December 17, 2010, as revised by Boeing Special Attention Service Bulletin 737-52-1154, Revision 1, dated August 3, 2011; except as provided by paragraph (u)(2) of this AD. Do all applicable related investigative and corrective actions at the applicable time specified in Tables 1 and 2 of paragraph 1.E., “Compliance,” of Boeing Alert Service Bulletin 737-52A1153, dated July 13, 2011, except as provided by paragraph (u)(1) of this AD. If no cracking is found during the inspections specified in Boeing Alert Service Bulletin 737-52A1153, dated July 13, 2011, at the applicable time specified in Tables 1 and 2 of paragraph 1.E., “Compliance,” of Boeing Alert Service Bulletin 737-52A1153, dated July 13, 2011, except as provided by paragraph (u)(1) of this AD, do the modification in accordance with Parts 5 and 6, as applicable, of the Accomplishment Instructions of Boeing Alert Service Bulletin 737-52A1153, dated July 13, 2011. Repeat the inspections thereafter at the times specified in Tables 1 and 2 of paragraph 1.E., “Compliance,” of Boeing Alert Service Bulletin 737-52A1153, dated July 13, 2011, until the preventative modification or repair is done to both ends of cross beam E in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 737-52A1153, dated July 13, 2011. Doing the inspection specified in this paragraph terminates the inspections required by paragraphs (h) and (k) of this AD.
(2) Where Boeing Special Attention Service Bulletin 737-52-1154, dated December 17, 2010; and Boeing Special Attention Service Bulletin 737-52-1154, dated December 17, 2010, as revised by Boeing Special Attention Service Bulletin 737-52-1154, Revision 1, dated August 3, 2011, specify to contact Boeing for repair, before further flight, repair using a method approved in accordance with the procedures specified in paragraph (x) of this AD.Start Printed Page 47555
(4) This AD does not require accomplishment of the access and restoration procedures identified in the Work Instructions of Boeing Alert Service Bulletin 737-52A1079, Revision 7, dated December 17, 2010; Boeing Alert Service Bulletin 737-52A1153, dated July 13, 2011; Boeing Special Attention Service Bulletin 737-52-1154, dated December 17, 2010; and Boeing Special Attention Service Bulletin 737-52-1154, dated December 17, 2010, as revised by Boeing Special Attention Service Bulletin 737-52-1154, Revision 1, dated August 3, 2011.
(1) The supplemental structural inspections specified in Tables 5 and 6 of paragraph 1.E., “Compliance,” of Boeing Alert Service Bulletin 737-52A1153, dated July 13, 2011; and Tables 3 and 4 of paragraph 1.E., “Compliance,” of Boeing Alert Service Bulletin 737-52A1079, Revision 7, dated December 17, 2010; and Table 5 of paragraph 1.E., “Compliance,” of Boeing Service Bulletin 737-52-1154, dated December 17, 2010, as revised by Boeing Special Attention Service Bulletin 737-52-1154, Revision 1, dated August 3, 2011, are not required by this AD.
(2) The damage tolerance inspections specified in Tables 5 and 6 of paragraph 1.E., “Compliance,” of Boeing Alert Service Bulletin 737-52A1153, dated July 13, 2011; and Tables 3 and 4 of paragraph 1.E., “Compliance,” of Boeing Alert Service Bulletin 737-52A1079, Revision 7, dated December 17, 2010; and Table 5 of paragraph 1.E., “Compliance,” of Boeing Service Bulletin 737-52-1154, dated December 17, 2010, as revised by Boeing Special Attention Service Bulletin 737-52-1154, Revision 1, dated August 3, 2011; may be used in support of compliance with section 121.1109(c)(2) or 129.109(b)(2) of the Federal Aviation Regulations (14 CFR 121.1109(c)(2) or 14 CFR 129.109(b)(2)). The corresponding actions specified in the Accomplishment Instructions and figures of Boeing Alert Service Bulletin 737-52A1153, dated July 13, 2011; and Boeing Alert Service Bulletin 737-52A1079, Revision 7, dated December 17, 2010; are not required by this AD.
(1) This paragraph provides credit for actions required by paragraphs (p), (q), and (r) of this AD, if the actions were accomplished before the effective date of this AD using any service information specified in paragraph (w)(1)(i), (w)(1)(ii), (w)(1)(iii), (w)(1)(iv), (w)(1)(v), (w)(1)(vi), or (w)(1)(vii) of this AD.
(i) Boeing Service Bulletin 737-52-1079, dated December 16, 1983.
(ii) Boeing Service Bulletin 737-52-1079, Revision 1, dated December 15, 1988.
(iii) Boeing Service Bulletin 737-52-1079, Revision 2, dated July 20, 1989.
(iv) Boeing Service Bulletin 737-52-1079, Revision 3, dated May 17, 1990.
(v) Boeing Service Bulletin 737-52-1079, Revision 4, dated February 21, 1991.
(vi) Boeing Service Bulletin 737-52-1079, Revision 5, dated May 16, 1996.
(vii) Boeing Alert Service Bulletin 737-52A1079, Revision 6, dated November 18, 1999.
(2) This paragraph provides credit for actions required by paragraphs (s) and (t) of this AD, if the actions were accomplished before the effective date of this AD using Boeing Service Bulletin 737-52-1154, dated December 17, 2010, provided that any alternative detailed inspections specified in Part 17 of the Accomplishment Instructions of Boeing Service Bulletin 737-52-1154, dated December 17, 2010, were done in accordance with Part 11 of the Accomplishment Instructions of Boeing Service Bulletin 737-52-1154, dated December 17, 2010.
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.
(3) The following service information was approved for IBR on September 10, 2013.
(i) Boeing Alert Service Bulletin 737-52A1153, dated July 13, 2011.
(ii) Boeing Alert Service Bulletin 737-52A1079, Revision 7, dated December 17, 2010.
(iii) Boeing Special Attention Service Bulletin 737-52-1154, dated December 17, 2010.
(iv) Boeing Special Attention Service Bulletin 737-52-1154, Revision 1, dated August 3, 2011.
(4) The following service information was approved for IBR on May 9, 2000 (65 FR 17583, April 4, 2000).
(i) Boeing Alert Service Bulletin 737-52A1079, Revision 6, dated November 18, 1999.
(5) The following service information was approved for IBR on December 24, 1998 (63 FR 67769, December 9, 1998).
(i) Boeing Service Bulletin 737-52-1079, Revision 5, dated May 16, 1996.
(6) 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.
(7) You may view this service information at FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, Washington 98057-3356. For information on the availability of this material at the FAA, call 425-227-1221.
(8) You may view this service information that is incorporated by reference at the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, call 202-741-6030, or go to http://www.archives.gov/​federal-register/​cfr/​ibr-locations.html.
Issued in Renton, Washington, on June 18, 2013.
[FR Doc. 2013-18765 Filed 8-5-13; 8:45 am]