Source: https://www.federalregister.gov/documents/2005/09/22/05-18785/airworthiness-directives-boeing-model-767-200--300-and--300f-series-airplanes-powered-by-general
Timestamp: 2018-03-21 05:53:28
Document Index: 105798155

Matched Legal Cases: ['art 39', '§\u200939', 'art 3', 'art 1', 'art 2', 'art 1', 'art 2', 'art 51']

Federal Register :: Airworthiness Directives; Boeing Model 767-200, -300, and -300F Series Airplanes Powered by General Electric or Pratt & Whitney Engines
Airworthiness Directives; Boeing Model 767-200, -300, and -300F Series Airplanes Powered by General Electric or Pratt & Whitney Engines
55519-55524 (6 pages)
Amendment 39-14288
AD 2005-19-23
Request To Remove Airplane Reference From Applicability
Request To Include Inspection Requirements for Airplanes With CRES Repair Strap
Explanation of Change Made to Paragraph (i)
https://www.federalregister.gov/d/05-18785 https://www.federalregister.gov/d/05-18785
The FAA is superseding an existing airworthiness directive (AD), which applies to certain Boeing Model 767 series airplanes. That AD currently requires repetitive inspections to detect discrepancies of the eight aft-most fastener holes in the horizontal tangs of the midspar fitting of the strut, and corrective actions if necessary. That AD also provides an optional terminating action for the repetitive inspections. Start Printed Page 55520This new AD adds repetitive inspections for cracks of the closeout angle that covers the two aft-most fasteners in the lower tang of the midspar fitting, and related investigative and corrective actions if necessary. This AD also reduces the inspection interval of the upper tang of the outboard midspar fitting; and provides an optional terminating action for the repetitive inspections. This AD results from a report of a crack in a closeout angle that covers the two aft-most fasteners in the lower tang of the midspar fitting; and the discovery of a crack in the lower tang of the midspar fitting under the cracked closeout angle. We are issuing this AD to prevent fatigue cracking in the primary strut structure and reduced structural integrity of the strut, which could result in separation of the strut and engine.
The Director of the Federal Register approved the incorporation by reference of Boeing Alert Service Bulletin 767-54A0101, Revision 4, dated February 10, 2005, listed in the AD as of October 27, 2005.
On June 9, 2004 (69 FR 24947, May 5, 2004), the Director of the Federal Register approved the incorporation by reference of Boeing Service Bulletin 767-54A0101, Revision 3, dated September 5, 2002.
On May 15, 2001 (66 FR 18523, April 10, 2001), the Director of the Federal Register approved the incorporation by reference of Boeing Service Bulletin 767-54A0101, Revision 1, dated February 3, 2000.
The FAA issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 to include an AD that supersedes AD 2004-09-14, amendment 39-13603 (69 FR 24947, May 5, 2004). The existing AD applies to certain Model 767 series airplanes. That NPRM was published in the Federal Register on June 3, 2005 (70 FR 32527). That NPRM proposed to continue to require repetitive inspections to detect discrepancies of the eight aft-most fastener holes in the horizontal tangs of the midspar fitting of the strut, and corrective actions if necessary. That NPRM also proposed to require repetitive inspections for cracks of the closeout angle that covers the two aft-most fasteners in the lower tang of the midspar fitting, and related investigative and corrective actions if necessary. That NPRM also proposed to reduce the inspection interval of the upper tang of the outboard midspar fitting; and to provide an optional terminating action for the repetitive inspections.
The airplane manufacturer requests that we remove the reference to Boeing Model 767-400ER series airplanes from the applicability of the NPRM. The commenter points out that these airplanes have improved corrosion resistant steel (CRES) mid-spar fittings.
We agree with the commenter. The Model 767-400ER series airplanes are not included in the effectivity of the Boeing Alert Service Bulletin 767-54A0101, Revision 4, dated February 10, 2005 (which was cited as the appropriate source of service information for doing the actions in the NPRM), but were inadvertently included in the applicability of the NPRM. We have changed the final rule to remove this model designation from the applicability.
The same commenter points out that some airplanes have had the closeout angle previously repaired by the addition of a CRES repair strap. This repair strap covers two aft-most bolts of the closeout angle at the midspar fitting. The commenter states that the repair strap prevents high-frequency eddy current inspections of the closeout angle. The commenter requests that the final rule include inspection requirements for these airplanes.
We partially agree with the commenter. We agree that additional inspections may be required for these airplanes. We disagree with including inspection requirements for these airplanes in the final rule. In accordance with 14 CFR 39.17, if the original airplane configuration is altered, modified, or repaired in any way that may affect the ability to accomplish the actions of an AD, the operator should apply for an alternative method of compliance (AMOC) through the FAA. Information about AMOCs is included in paragraph (q) of the final rule. We have not changed the final rule in this regard.
We have simplified paragraph (i) of the final rule by referring to the “Alternative Methods of Compliance (AMOCs)” paragraph of this AD for repair methods.
The following table provides the estimated costs for U.S. operators to comply with this AD. Start Printed Page 55521
Option 2: HFEC inspection (required by AD 2004-09-14) 3 $65 None $195, per inspection cycle 263 N/A (depends on chosen option).
HFEC inspection (new proposed action) 4 $65 None $260, per inspection cycle 263 $68,380, per inspection cycle.
2. The Federal Aviation Administration (FAA) amends § 39.13 by removing amendment 39-13603 ( 69 FR 24947, May 5, 2004) and by adding the following new airworthiness directive (AD):
2005-19-23 Boeing: Amendment 39-14288. Docket No. FAA-2005-21355; Directorate Identifier 2005-NM-037-AD.
(b) This AD supersedes AD 2004-09-14.
(c) This AD applies to Boeing Model 767-200, -300, and -300F series airplanes, certificated in any category, as identified in Boeing Alert Service Bulletin 767-54A0101, Revision 4, dated February 10, 2005.
(i) If no cracking is detected and the fastener hole diameter is less than or equal to 0.5322 inch, before further flight, rework the hole in accordance with Part 3 of the Accomplishment Instructions of the service bulletin. Start Printed Page 55522
(i) If any discrepancies (cracking, incorrect fastener hole diameter) are detected during any inspection required by paragraph (f) or (p) of this AD, for which the service bulletin specifies that the manufacturer may be contacted for disposition of those repair conditions: Before further flight, accomplish the applicable related investigative and corrective actions (including fastener hole rework and/or midspar fitting replacement) using a method approved in accordance with the procedures specified in paragraph (q) of this AD.
(l) If no cracking or discrepancy is detected during any HFEC inspection required by paragraph (j) of this AD or by this paragraph of this AD: Perform the follow-on actions specified in paragraph (f)(2)(i) or (f)(2)(ii) of this AD, as applicable, per the Accomplishment Instructions in Boeing Service Bulletin 767-54A0101, Revision 3, dated September 5, 2002; or Boeing Alert Service Bulletin 767-54A0101, Revision 4, dated February 10, 2005; and repeat the inspections of all eight aft-most fastener holes thereafter at the applicable intervals specified in Table 1 of this AD.
(1) All eight aft-most fastener holes were inspected per paragraph (j) of this AD: At the applicable intervals specified in Table 1, “Reinspection Intervals for Part 1,” or Table 2, “Reinspection Intervals for Part 2,” as applicable. Both tables are included in Figure 1 of the applicable service bulletin.
Within 1,500 flight cycles after the effective date of this AD, only the repetitive intervals in Boeing Alert Service Bulletin 767-54A0101, Revision 4, dated February 10, 2005, may be used.
(2) Only the four forward fastener holes in the group of eight aft-most fastener holes were inspected per paragraph (j) of this AD: At the next scheduled repetitive inspection required by paragraph (f)(1) of (f)(2) of this AD, as applicable. Thereafter at the applicable intervals specified in Table 1, “Reinspection Intervals for Part 1,” or Table 2, “Reinspection Intervals for Part 2,” as applicable. Both tables are included in Figure 1 of the applicable service bulletin.
(n) Accomplishing the terminating action in paragraph (h)(1) of this AD before June 9, 2004, in accordance with the service bulletin revisions in Table 2 of this AD, is acceptable for compliance with the requirements of this AD. After the effective date of this AD, only Boeing Alert Service Bulletin 767-54A0101, Revision 4, dated February 10, 2005, may be used for accomplishing the terminating action in paragraph (h)(1) of this AD.
Table 2.—Service Bulletins for Terminating Action
(o) Inspections required by paragraphs (f) and (g) of this AD that are accomplished before June 9, 2004, in accordance with the service bulletin revisions in Table 3 of this AD are considered acceptable for compliance with the corresponding action specified in this AD. Start Printed Page 55523
Table 3.—Service Bulletins for Previously Accomplished Inspections
767-54-0074 Original March 27, 1997 Nacelles/Pylons—Strut Attach Fuse Pins—Upper link Fuse Pin Inspection/Replacement. Where this service bulletin refers to a cotter pin with part number (P/N) MS25665-374, the P/N should be MS24665-374. Where this service bulletin says, “If no crack indication is found, reinstall the fuse pin,” the correct statement is “If no crack indication is found, continue to Step F.”
AD 94-11-02, amendment 39-8918, (59 FR 27229, May 26, 1994) All Boeing Model 767 series airplanes 767-54A0062 Repetitive detailed visual and eddy current inspections to detect cracks of certain midspar fuse pins, and replacement of any cracked midspar fuse pin with a new fuse pin.
AD 2000-10-51, amendment 39-11770 (65 FR 37011, June 13, 2000) Certain Boeing Model 767 series airplances 767-54-0074 One-time inspection to determine whether certain bolts are installed in the side load underwing fittings on both struts, and various follow-on actions, if necessary.
AD 2001-02-07, amendment 39-12091 (66 FR 8085, January 29, 2001) Certain Boeing Model 767 series airplanes powered by Pratt & Whitney engines 767-54-0069, 767-54-0080, and 767-54-0094 Modification of the nacelle strut and wing structure. Terminates certain requirements of AD 94-11-02.
AD 2001-06-12, amendment 39-12159 (66 FR 17492, April 2, 2001) Certain Boeing Model 767 series airplanes powered by General Electric engines 767-54-0069, 767-54-0081, and 767-54-0094 Modification of the nacelle strut and wing structure. Terminates certain requirements of AD 94-11-02.
AD 2003-03-02, amendment 39-13026 (68 FR 4374, January 29, 2003) All Boeing Model 767 series airplanes 767-54A0062 Supersedes AD 94-11-02; Retains all requirements but reduces certain compliance times for certain inspections, expands the detailed and eddy current inspections, and limits the applicability.
(q)(1) The Manager, Seattle ACO, FAA, has the authority to approve AMOCs for this AD, if requested in accordance with the procedures found in 14 CFR 39.19.
(r) You must use the service information identified in Table 6 of this AD to perform the actions that are required by this AD, unless the AD specifies otherwise.
(1) The Director of the Federal Register approved the incorporation by reference of Boeing Alert Service Bulletin 767-54A0101, Revision 4, dated February 10, 2005, in accordance with 5 U.S.C. 552(a) and 1 CFR part 51.
(2) On June 9, 2004 (69 FR 24947, May 5, 2004), the Director of the Federal Register approved the incorporation by of Boeing Service Bulletin 767-54A0101, Revision 3, dated September 5, 2002.
(3) On May 15, 2001 (66 FR 18523, April 10, 2001), the Director of the Federal Register approved the incorporation by reference of Boeing Service Bulletin 767-54A0101, Revision 1, dated February 3, 2000.
[FR Doc. 05-18785 Filed 9-21-05; 8:45 am]