Source: https://www.federalregister.gov/documents/2009/03/11/E9-4734/airworthiness-directives-boeing-model-737-300--400-and--500-series-airplanes
Timestamp: 2018-07-20 23:01:45
Document Index: 94413632

Matched Legal Cases: ['art 39', 'art 3', 'art 4', 'art 4', 'art 5', 'art 5', 'art 5', 'art 3', 'art 5']

This AD is effective April 15, 2009.
10469-10471 (3 pages)
Amendment 39-15796
AD 2009-02-06
Request To Revise Paragraph (h) To Correct References to Parts of the Service Bulletin
Request To Revise Paragraph (e) To Clarify Compliance Times
https://www.federalregister.gov/d/E9-4734 https://www.federalregister.gov/d/E9-4734
We are adopting a new airworthiness directive (AD) for certain Boeing Model 737-300, -400, and -500 series airplanes. This AD requires repetitive high frequency eddy current inspections for cracking of the 1.04-inch nominal diameter wire penetration hole in the frame and frame reinforcement, between stringers S-20 and S-21, on both the left and right sides of the airplane, and related investigative and corrective actions if necessary. This AD results from reports of cracking in the frame, or in the frame and frame reinforcement, common to the 1.04-inch nominal diameter wire penetration hole intended for wire routing. We are issuing this AD to detect and correct cracking in the fuselage frames and frame reinforcements, which could reduce the structural capability of the frames to sustain limit loads, and result in cracking in the fuselage skin and subsequent rapid depressurization of the airplane.
The Director of the Federal Register approved the incorporation by reference of a certain publication listed in this AD as of April 15, 2009.
We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 to include an airworthiness directive (AD) that would apply to certain Boeing Model 737-300, -400, and -500 series airplanes. That NPRM was published in the Federal Register on June 24, 2008 (73 FR 35598). That NPRM proposed to require repetitive high frequency eddy current (HFEC) inspections for cracking of the 1.04-inch nominal diameter wire penetration hole in the frame and frame reinforcement, between stringers S-20 and S-21, on both the left and right sides of the airplane, and related investigative and corrective actions if necessary.
KLM Royal Dutch Airlines (KLM) requests that we revise paragraph (h) of the NPRM to correct the references to certain parts of Boeing Alert Service Bulletin 737-53A1279, dated December 18, 2007 (“the service bulletin”), for doing certain actions. KLM points out that paragraph (h) of the NPRM refers to Part 3 of the service bulletin for doing the repair and to Part 4 of the service bulletin for doing the preventative modification. KLM further points out that Part 4 of the service bulletin concerns repeat inspections, not the preventative modification. The preventative modification is provided in Part 5 of the service bulletin.
We agree with the commenter. It was our intention to refer to Part 5 of the service bulletin for doing the preventative modification provided in paragraph (h) of the NPRM. Therefore, we have revised paragraph (h) of this AD to refer to Part 5 of the service bulletin for doing the preventative modification.
KLM requests that we revise paragraph (e) of the NPRM to refer to paragraph 1.E., “Compliance,” of the service bulletin. KLM asserts that adding a reference to the location of the compliance times in the service bulletin would be helpful.
We do not agree to revise paragraph (e) of this AD. A reference to paragraph 1.E., “Compliance,” of Boeing Service Bulletin 737-53A1279, dated December 18, 2007, is already provided in paragraph (g) of this AD.
We estimate that this AD affects 616 airplanes of U.S. registry. The following table provides the estimated costs for U.S. operators to comply with this AD. The average labor rate is $80 per work hour.
(1) Is not a “significant regulatory action” under Executive Order 12866, (2) Is not a “significant rule” under DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979), andStart Printed Page 10471
2009-02-06 Boeing: Amendment 39-15796. Docket No. FAA-2008-0671; Directorate Identifier 2008-NM-017-AD.
(a) This airworthiness directive (AD) is effective April 15, 2009.
(1) The “condition” column of paragraph 1.E. of Boeing Alert Service Bulletin 737-53A1279, dated December 18, 2007, refers to total flight cycles “at the date given on this service bulletin.” This AD applies to the airplanes with the specified total flight cycles as of the effective date of this AD.
(g) At the applicable time specified in paragraph 1.E., “Compliance,” of the service bulletin, except as specified by paragraph (f)(1) of this AD: Do a high frequency eddy current (HFEC) surface inspection or an HFEC hole/edge inspection for cracking of the 1.04-inch nominal diameter wire penetration hole in the frame and frame reinforcement, between stringer S-20 and S-21; and do all applicable related investigative and corrective actions; by accomplishing all the actions specified in the Accomplishment Instructions of the service bulletin, except as specified by paragraphs (f)(2) and (f)(3) of this AD. Do all applicable related investigative and corrective actions before further flight. Thereafter, repeat the inspections at the applicable intervals specified in paragraph 1.E. of the service bulletin.
(h) Doing the repair in Part 3 or the preventative modification in Part 5 of the service bulletin terminates the repetitive inspection requirements of this AD.
(j) You must use Boeing Alert Service Bulletin 737-53A1279, dated December 18, 2007, to do the actions required by this AD, unless the AD specifies otherwise.
(3) You may review copies of the service information incorporated by reference 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 or 425-227-1152.
[FR Doc. E9-4734 Filed 3-10-09; 8:45 am]