Source: https://regulations.vlex.com/vid/airworthiness-directives-310404182
Timestamp: 2019-11-13 11:41:44
Document Index: 733132431

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Airworthiness Directives: - August 05, 2011 - Regulations - VLEX 310404182
Pages 47522-47527
FR Doc No: 2011-19904
Docket No. FAA-2011-0722; Directorate Identifier 2010-NM-262-AD
Airworthiness Directives; The Boeing Company Model 737-100, -200,
-200C, -300, -400, and -500 Series Airplanes
(AD) that applies to certain Model 737-100 and -200 series airplanes.
The existing AD currently requires various inspections for cracks in the outboard chord of the frame at body station (BS) 727 and in the outboard chord of stringer (S) 18A, and repair or replacement of cracked parts. Since we issued that AD, there have been several reports of fatigue cracking in the frame outboard chord at BS 727 and in the radius of the auxiliary chord on airplanes that were not affected by the existing AD. This proposed AD would add airplanes to the applicability statement in the existing AD and add inspections for cracks in the BS 727 frame outboard chords and the radius of the auxiliary chord, for certain airplanes. This proposed AD would also remove the inspections of the outboard chord of S-18A required by the existing AD. We are proposing this AD to detect and correct fatigue cracking of the outboard and auxiliary chords, which
could result in reduced structural integrity of the outboard chord and consequent rapid decompression of the airplane.
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; e-mail 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.
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; e-mail 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-2011-0722;
Directorate Identifier 2010-NM-262-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.
We reviewed Boeing Alert Service Bulletin 737-53A1166, Revision 2, dated May 25, 2006. The existing AD refers to Boeing Alert Service
Bulletin 737-53A1166, dated June 30, 1994; and Boeing Service Bulletin 737-53A1166, Revision 1, dated May 25, 1995; for accomplishing the required actions. Revision 1 of this service bulletin was issued to include airplanes having 7075-T73 frame outboard chords. Revision 2 of this service bulletin expands the effectivity in Revision 1 of this service bulletin, and adds inspections for cracks of the 7075-T73 frame outboard chord and in the radius of the auxiliary chord, and repair or replacement if necessary.
This proposed AD would retain certain requirements of AD 95-12-17.
This proposed AD would add airplanes to the applicability statement in the existing AD. This proposed AD would also remove the inspections of the outboard chord of S-18A required by the existing AD, and add inspections for cracks in the BS 727 frame outboard chords and the radius of the auxiliary chord, for certain airplanes. This proposed AD would require accomplishing the actions specified in the service information described previously, except as discussed under
``Difference Between the Proposed AD and the Service Information.''
paragraph (a).......................................
paragraph (g) paragraph (b).......................................
paragraph (h) paragraph (c).......................................
paragraph (i) paragraph (d).......................................
paragraph (j) paragraph (e).......................................
removed paragraph (f).......................................
paragraph (k) paragraph (g).......................................
Cost on U.S. Number of U.S.
Various inspections (retained 4 work-hours x
$0 $340 per
$100,640 per
296 actions from existing AD).
cycle. inspection cycle.
Ultrasonic inspection (new
13 work-hours x
0 1,105 per
634,270 per
574 proposed action).
$1,105 per
Detailed and HFEC inspections 13 work-hours x
(new proposed actions).
Optional modification (retained action from
50 work-hours x $85 per hour =
$7,930 existing AD).
Repair of cracking of the outboard chord frame 514 work-hours x $85 per hour =
$42,690.
Time-limited repair cracking of the outboard 63 work-hours x $85 per hour =
8,087 chord frame.
Repair of cracking of the outboard chord...... 49 work-hours x $85 per hour =
Sec. 39.13 [Amended] 2. The FAA amends Sec. 39.13 by removing airworthiness directive
(AD) 95-12-17, Amendment 39-9268 (60 FR 36981, July 19, 1995), and adding the following new AD:
(a) The FAA must receive comments on this AD action by September 19, 2011.
(c) This AD applies to all The Boeing Company Model 737-100, - 200, -200C, -300, -400, and -500 series airplanes, certificated in any category.
Association (ATA) of America Code 53, Fuselage.
Restatement of Certain Requirements of AD 95-12-17 With Revised Service
Information: Repetitive Inspections and Repair or Replacement
(g) For Model 737-100 and -200 series airplanes on which the BS 727 frame upper outboard chord has been replaced in accordance with
Boeing Service Bulletin 737-53-1088: Prior to the accumulation of 30,000 total flight cycles since replacement of the upper outboard chord, or within 4,500 flight cycles after August 18, 1995 (the effective date of AD 95-12-17), whichever occurs later, perform close visual, pulse echo shear wave (PESW), and high frequency eddy current (HFEC) inspections to detect cracks in the outboard chord of the frame at BS 727, in accordance with Part I of the Accomplishment
Instructions of Boeing Alert Service Bulletin 737-53A1166, dated
June 30, 1994; Boeing Service Bulletin 737-53A1166, Revision 1, dated May 25, 1995; or Boeing Alert Service Bulletin 737-53A1166,
Revision 2, dated May 25, 2006; as applicable. As of the effective date of this AD use only Revision 2 of this service bulletin.
(h) For Model 737-100 and -200 series airplanes on which the BS 727 frame upper outboard chord has been replaced in accordance with
Boeing Service Bulletin 737-53-1088: Repeat the inspections required by paragraph (g) of this AD at the time specified in paragraphs
(h)(1), (h)(2), (h)(3), and (h)(4) of this AD, as applicable, until the optional terminating action described in paragraph (l) of this
AD is accomplished.
(4) If, at the time of the most recent inspection required by paragraph (g) or (h) of this AD, the airplane has accumulated 70,000 or more total flight cycles since replacement of the outboard chord:
Perform the next inspection within 3,000 flight cycles. Repeat the inspection thereafter at intervals not to exceed 3,000 flight cycles.
(i) For Model 737-100 and -200 series airplanes on which the BS 727 frame outboard chord has not been replaced, or on which only the lower outboard chord has been replaced in accordance with Boeing
Service Bulletin 737-53-1088: Perform close visual, PESW, and HFEC inspections to detect cracks in the outboard chord of the frame at
BS 727, in accordance with Part I of the Accomplishment Instructions of Boeing Alert Service Bulletin 737-53A1166, dated June 30, 1994;
Boeing Service Bulletin 737-53A1166, Revision 1, dated May 25, 1995; or Boeing Alert Service Bulletin 737-53A1166, Revision 2, dated May 25, 2006; as applicable. As of the effective date of this AD, use only Revision 2 of this service bulletin. Perform these inspections initially at the time specified in paragraph (i)(1), (i)(2), (i)(3), or (i)(4), as applicable. Repeat these inspections thereafter at the intervals specified in paragraph (j) of this AD.
(1) For airplanes that have accumulated 27,000 or more total flight cycles, but fewer than 50,000 total flight cycles, as of
August 18, 1995: Inspect prior within 4,500 flight cycles after
(2) For airplanes that have accumulated 50,000 or more total flight cycles, but fewer than 60,000 total flight cycles, as of
August 18, 1995: Inspect prior to the accumulation of 2,500 flight cycles after August 18, 1995.
(3) For airplanes that have accumulated 60,000 or more total flight cycles, but fewer than 70,000 total flight cycles as of
August 18, 1995: Inspect prior to the accumulation of 1,500 flight cycles after August 18, 1995.
(j) Repeat the inspections required by paragraph (i) of this AD at the time specified in paragraphs (j)(1), (j)(2), (j)(3), and
(j)(4) of this AD, as applicable, until the optional terminating action described in paragraph (l) of this AD is accomplished:
(1) If, at the time of the most recent inspection required by paragraph (i) or (j) of this AD, the airplane has accumulated 27,000 or more total flight cycles, but fewer than 50,000 total flight cycles: Perform the next inspection within 15,000 flight cycles.
Repeat the inspection thereafter at intervals not to exceed 15,000 flight cycles until the airplane has accumulated 50,000 or more total flight cycles. Do the inspections required by paragraph (j)(2) of this AD at the time specified.
(2) If, at the time of the most recent inspection required by paragraph (i) or (j) of this AD, the airplane had accumulated 50,000 or more total flight cycles, but fewer than 60,000 total flight cycles: Perform the next inspection within 7,500 flight cycles.
Repeat the inspection thereafter at intervals not to exceed 7,500 flight cycles until the airplane has accumulated 60,000 or more total flight cycles. Do the inspections required by paragraph (j)(3) of this AD at the time specified.
(3) If, at the time of the most recent inspection required by paragraph (i) or (j) of this AD, the airplane had accumulated 60,000 or more total flight cycles, but fewer than 70,000 total flight cycles: Perform the next inspection within 5,000 flight cycles.
Repeat the inspection thereafter at intervals not to exceed 5,000 flight cycles until the airplane has accumulated 70,000 or more total flight cycles. Do the inspections required by paragraph (j)(4) of this AD at the time specified.
(k) If any crack is found in the outboard chord of the frame at
BS 727 during any inspection required by paragraphs (g) through (j) of this AD, accomplish paragraph (k)(1) or (k)(2) of this AD, as applicable, in accordance with Boeing Alert Service Bulletin 737- 53A1166, dated June 30, 1994; Boeing Service Bulletin 737-53A1166,
Revision 1, dated May 25, 1995; or Boeing Alert Service Bulletin 737-53A1166, Revision 2, dated May 25, 2006; as applicable. As of the effective date of this AD, use only Revision 2 of this service bulletin.
(1) For any crack that extends from the forward edge of the chord or from the forward fastener hole, but that does not
extend past the second fastener hole, accomplish either paragraph
(l)(1)(i) or (l)(1)(ii) of this AD. Thereafter, perform initial and repetitive inspections in accordance with paragraphs (g) and (h) of this AD.
(i) Prior to further flight, install the time limited repair.
Within 4,500 flight cycles or within 18 months after accomplishing the time-limited repair, whichever occurs first, replace the outboard chord. Or
Note 1: Boeing Alert Service Bulletin 737-53A1166, dated June 30, 1994; Boeing Service Bulletin 737-53A1166, Revision 1, dated May 25, 1995; and Boeing Alert Service Bulletin 737-53A1166, Revision 2, dated May 25, 2006; refer to Boeing Service Bulletin 737-53-1088 as an additional source of guidance for procedures to replace the chord.
(2) For any crack that extends from the forward edge of the chord, or from the forward fastener hole, and that extends past the second fastener hole, prior to further flight, replace the outboard chord in accordance with Boeing Alert Service Bulletin 737-53A1166, dated June 30, 1994; Boeing Service Bulletin 737-53A1166, Revision 1, dated May 25, 1995; or Boeing Alert Service Bulletin 737-53A1166,
Revision 2, dated May 25, 2006; as applicable. As of the effective date of this AD, use only Revision 2 of this service bulletin.
Thereafter, perform initial and repetitive inspections in accordance with paragraphs (g) and (h) of this AD.
(l) For airplanes identified in table 5 of paragraph 1.E.,
``Compliance'' of Boeing Alert Service Bulletin 737-53A1166,
Revision 2, dated May 25, 2006: Before the accumulation of 27,000 total flight cycles, or within 5,000 flight cycles after the effective date of this AD, whichever occurs later, do internal detailed and HFEC inspections to detect cracks in the auxiliary chord radius of the frame at BS 727, in accordance with Part 1 of the Accomplishment Instructions of Boeing Alert Service Bulletin 737-53A1166, Revision 2, dated May 25, 2006. Repeat the inspections thereafter at intervals not to exceed 15,000 flight cycles until the optional terminating action described in paragraph (r) of this AD is accomplished. If any crack is found, before further flight, repair in accordance with the requirements in paragraph (p) of this AD.
(m) For airplanes identified in table 2 of paragraph 1.E.,
Revision 2, dated May 25, 2006: Do the applicable inspections required by paragraph (m)(1) or (m)(2) of this AD at the time specified, in accordance with Part 1 of the Accomplishment
Instructions of Boeing Alert Service Bulletin 737-53A1166, Revision 2, dated May 25, 2006. Except as required by paragraph (p) of this
AD, if any crack is found during any inspection required by paragraph (m)(1) or (m)(2) of this AD, before further flight, repair in accordance with Part 3 or Part 4 of the Accomplishment
Instructions of Boeing Alert Service Bulletin 737-53A1166, Revision 2, dated May 25, 2006, as applicable. Repeat the inspections until the optional terminating action described in paragraph (r) of this
(1) For airplanes on which the inspections specified in Boeing
Alert Service Bulletin 737-53A1166, dated June 30, 1994; or Boeing
Service Bulletin 737-53A1166, Revision 1, dated May 25, 1995; have not been performed as of the effective date of this AD: Do the inspections required by paragraphs (m)(1)(i) and (m)(1)(ii) of this
AD at the time specified.
(2) For airplanes on which the inspections specified in Boeing
Service Bulletin 737-53A1166, Revision 1, dated May 25, 1995; have been performed as of the effective date of this AD: Repeat the applicable inspection specified in paragraphs (m)(1)(i) and
(m)(1)(ii) of this AD thereafter at intervals not to exceed 5,000 flight cycles for the ultrasonic and surface HFEC inspections, and at intervals not to exceed 15,000 flight cycles for the open hole eddy current inspection.
(n) For airplanes identified in table 3 of paragraph 1.E.,
Revision 2, dated May 25, 2006: Do the applicable inspections required by paragraph (n)(1) or (n)(2) of this AD at the time specified, in accordance with Part 1 of the Accomplishment
AD, if any crack is found during any inspection required by paragraphs (n)(1) or (n)(2) of this AD, before further flight, repair in accordance with Part 3 or Part 4 of the Accomplishment
Service Bulletin 737-53A1166, Revision 1, dated May 25, 1995; have not been done as of the effective date of this AD: Do the inspections required by paragraphs (n)(1)(i) and (n)(1)(ii) of this
Service Bulletin 737-53A1166, Revision 1, dated May 25, 1995; have been done as of the effective date of this AD: Repeat the applicable inspection specified in paragraphs (n)(1)(i) and (n)(1)(ii) of this
AD thereafter at intervals not to exceed 5,000 flight cycles for the ultrasonic, low frequency eddy current, and edge HFEC inspections, and at intervals not to exceed 15,000 flight cycles for the open hole eddy current inspection.
(o) For airplanes identified in table 4 of paragraph 1.E.,
Revision 2, dated May 25, 2006: Before the accumulation of 50,000 or more total flight cycles, but fewer than or equal to 60,000 total flight cycles, after accomplishing the modification of the outboard chord of the frame at BS 727 at S-18A: Do a one-time follow-on open hole eddy current inspection to detect cracks in the modified chord in accordance with Part 8 of the Accomplishment Instructions of
Boeing Alert Service Bulletin 737-53A1166, Revision 2, dated May 25, 2006.
(p) If any crack is found during any inspection required by paragraphs (l) through (o) of this AD, and the repairs specified in
Part 3 and Part 4 of the Accomplishment Instructions of Boeing Alert
Service Bulletin 737-53A1166, Revision 2, dated May 25, 2006, can not be installed using the procedures identified in this service bulletin: Before further flight, repair using a method approved in accordance with the procedures specified in paragraph (s) of this
(q) For any airplane on which a time-limited repair is installed on the outboard chord of the frame at body station BS 727 in accordance with Boeing Alert Service Bulletin 737-53A1166, dated
June 30, 1994; or Boeing Service Bulletin 737-53A1166, Revision 1, dated May 25, 1995: Within 4,500 flight cycles after installation of the repair, or within 6 months after the effective date of this AD, whichever occurs later, replace the repair in accordance with Part 9 of the Accomplishment Instructions of Boeing Alert Service Bulletin 737-53A1166, Revision 2, dated May 25, 2006.
(r) Accomplishment of the applicable action specified in paragraph (r)(1) or (r)(2) of this AD, in accordance with Part 2 of the Accomplishment Instructions of Boeing Alert
Service Bulletin 737-53A1166, dated June 30, 1994; Boeing Service
Bulletin 737-53A1166, Revision 1, dated May 25, 1995; or Part 6 of the Accomplishment Instructions of Boeing Alert Service Bulletin 737-53A1166, Revision 2, dated May 25, 2006; constitutes terminating action for the inspections required by this AD.
(s)(1) The Manager, Seattle Aircraft Certification Office (ACO),
FAA, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. In accordance with 14
Flight Standards District Office, as appropriate. If sending information directly to the manager of the ACO, send it to the attention of the person identified in the Related Information section of this AD. Information may be e-mailed to: 9-ANM-Seattle-ACO-AMOC-Requests@faa.gov.
(ODA) that has been authorized by the Manager, Seattle ACO to make those findings. For a repair method to be approved, the repair must meet the certification basis of the airplane, and the approval must specifically refer to this AD.
(5) For airplanes identified in tables 2, 3, and 5 of paragraph 1.E., ``Compliance'' of Boeing Alert Service Bulletin 737-53A1166,
Revision 2, dated May 25, 2006: The Manager, Seattle ACO, approves the inspection methods, thresholds, and repetitive intervals therein as an AMOC for the inspections of Structurally Significant Items
(SSIs) F-29A and F-29B required by paragraphs (g) and (h) of AD 2008-08-23, Amendment 39-15477 (Boeing 737-100/200/200C Supplemental
Structural Inspection Document (SSID) D6-37089, Revision E, dated
May 1, 2007), and paragraphs (g) and (h) of AD 2008-09-13, Amendment 39-15494 (Boeing 737-400/500/600 SSID D6-82669, dated May 1, 2007).
This approval applies only to SSIs F-29A and F-29B of the applicable
SSID and only for the portions of the BS 727 outer chord that have been inspected or that have been repaired or modified in accordance with Boeing Alert Service Bulletin 737-53A1166, Revision 2, dated
May 25, 2006. All provisions of ADs 2008-08-23 and 2008-09-13 that are not specifically referenced in this paragraph remain fully applicable and must be done. If operators request this AMOC, they must revise their FAA-approved maintenance or inspection program to incorporate the alternative inspections in this paragraph.
(t) For more information about this AD, contact Alan Pohl,
Aerospace Engineer, Airframe Branch, ANM-120S, FAA, Seattle ACO, 1601 Lind Avenue, SW., Renton, Washington 98057-3356; phone: (425) 917-6450; fax: (425) 917-6590; e-mail: alan.pohl@faa.gov.
(u) For service information identified in this AD, contact
P.O. Box 3707, MC 2H-65, Seattle, Washington 98124-2207; telephone 206-544-5000, extension 1; fax 206-766-5680; e-mail me.boecom@boeing.com; Internet https://www.myboeingfleet.com. You may review copies of the referenced service information at the FAA,
FR Doc. 2011-19904 Filed 8-4-11; 8:45 am
Antidumping: Hot-rolled carbon steel flat products from Thailand,