Skip to Content

Rule

Airworthiness Directives; Boeing Model 727-100 and 727-200 Series Airplanes

Document Details

Information about this document as published in the Federal Register.

Published Document

This document has been published in the Federal Register. Use the PDF linked in the document sidebar for the official electronic format.

Start Preamble

AGENCY:

Federal Aviation Administration (FAA), DOT.

ACTION:

Final rule.

SUMMARY:

We are adopting a new airworthiness directive (AD) for certain Boeing Model 727-100 and 727-200 series airplanes. This AD requires repetitive internal and external high frequency eddy current, mid frequency eddy current, low frequency eddy current, and magneto optic imaging inspections to detect cracks, corrosion, delamination, and materials loss in the lower fastener row of the lower skin and the upper fastener row of the upper skin, and corrective actions if necessary. This AD results from a report of decompression in a Boeing Model 737 airplane at flight level 290. We are issuing this AD to detect and correct scratches and excessive reduction in material thickness from excessive blend-out or corrosion, which could lead to premature cracking in the lap joint. Such cracking could adversely affect the structural integrity of the airplane.

DATES:

This AD is effective April 28, 2009.

The Director of the Federal Register approved the incorporation by reference of a certain publication listed in the AD as of April 28, 2009.

ADDRESSES:

For service information identified in this AD, contact Boeing 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.

Examining the AD Docket

You may examine the AD docket on the Internet at http://www.regulations.gov; or in person at the Docket Management Facility between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this AD, the regulatory evaluation, any comments received, and other information. The address for the Docket Office (telephone 800-647-5527) is the Document Management Facility, U.S. Department of Transportation, Docket Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New Jersey Avenue, SE., Washington, DC 20590.

Start Further Info

FOR FURTHER INFORMATION CONTACT:

Berhane Alazar, Aerospace Engineer, Airframe Branch, ANM-120S, FAA, Seattle Aircraft Certification Office (ACO), 1601 Lind Avenue, SW., Renton, Washington 98057-3356; telephone (425) 917-6577; fax (425) 917-6590.

End Further Info End Preamble Start Supplemental Information

SUPPLEMENTARY INFORMATION:

Discussion

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 727-100 and 727-200 series airplanes. That NPRM was published in the Federal Register on October 17, 2008 (73 FR 61747). That NPRM proposed to require repetitive internal and external high frequency eddy current, mid frequency eddy Start Printed Page 12242current, low frequency eddy current, and magneto optic imaging inspections to detect cracks, corrosion, delamination, and materials loss in the lower fastener row of the lower skin and the upper fastener row of the upper skin, and corrective actions if necessary.

Comments

We gave the public the opportunity to participate in developing this AD. We considered the comment received. The commenter, Boeing, supports the NPRM.

Clarification of Paragraph (f)(1) of This AD

We have revised paragraph (f)(1) of this AD to clarify the exception to the compliance times in Boeing Alert Service Bulletin 727-53A0223, dated March 28, 2002.

Conclusion

We reviewed the relevant data, considered the comment received, and determined that air safety and the public interest require adopting the AD as proposed.

Costs of Compliance

We estimate that this AD affects 73 airplanes of U.S. registry. We also estimate that it would take 56 work hours per product to comply with this AD. The average labor rate is $80 per work hour. Based on these figures, we estimate the cost of this AD to the U.S. operators to be $327,040, or $4,480 per product, per inspection cycle.

Authority for This Rulemaking

Title 49 of the United States Code specifies the FAA's authority to issue rules on aviation safety. Subtitle I, section 106, describes the authority of the FAA Administrator. “Subtitle VII: Aviation Programs,” describes in more detail the scope of the Agency's authority.

We are issuing this rulemaking under the authority described in “Subtitle VII, Part 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.

Regulatory Findings

This AD will not have federalism implications under Executive Order 13132. This AD will not have a substantial direct effect on the States, on the relationship between the national government and the States, or on the distribution of power and responsibilities among the various levels of government.

For the reasons discussed above, I certify that this AD:

(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), and

(3) Will not have a significant economic impact, positive or negative, on a substantial number of small entities under the criteria of the Regulatory Flexibility Act.

You can find our regulatory evaluation and the estimated costs of compliance in the AD Docket.

Start List of Subjects

List of Subjects in 14 CFR Part 39

End List of Subjects

Adoption of the Amendment

Start Amendment Part

Accordingly, under the authority delegated to me by the Administrator, the FAA amends

End Amendment Part Start Part

PART 39—AIRWORTHINESS DIRECTIVES

End Part Start Amendment Part

1. The authority citation for part 39 continues to read as follows:

End Amendment Part Start Authority

Authority: 49 U.S.C. 106(g), 40113, 44701.

End Authority
[Amended]
Start Amendment Part

2. The FAA amends § 39.13 by adding the following new AD:

End Amendment Part

2009-06-10 Boeing: Amendment 39-15846. Docket No. FAA-2008-1103; Directorate Identifier 2008-NM-048-AD.

Effective Date

(a) This airworthiness directive (AD) is effective April 28, 2009.

Affected ADs

(b) None.

Applicability

(c) This AD applies to Boeing Model 727-100 and 727-200 series airplanes, certificated in any category; as identified in Boeing Alert Service Bulletin 727-53A0223, dated March 28, 2002.

Unsafe Condition

(d) This AD results from a report of decompression in a Boeing Model 737 airplane at flight level 290. We are issuing this AD to detect and correct scratches and excessive reduction in material thickness from excessive blend-out or corrosion, which could lead to premature cracking in the lap joint. Such cracking could adversely affect the structural integrity of the airplane.

Compliance

(e) Comply with this AD within the compliance times specified, unless already done.

Inspections and Corrective Actions

(f) Except as provided by paragraphs (f)(1), (f)(2), and (f)(3) of this AD: At the applicable compliance times and repeat intervals listed in paragraph 1.E., “Compliance,” of Boeing Alert Service Bulletin 727-53A0223, dated March 28, 2002 (“the service bulletin”), do repetitive internal and external high frequency eddy current, mid frequency eddy current, low frequency eddy current, and magneto optic imaging inspections to detect cracks, corrosion, delamination, and materials loss in the lower fastener row of the lower skin and the upper fastener row of the upper skin, and corrective actions by accomplishing all the applicable actions specified in the Accomplishment Instructions of the service bulletin. The applicable corrective actions must be done before further flight.

(1) Paragraph 1.E. of Boeing Alert Service Bulletin 727-53A0223, dated March 28, 2002, has the table column titled, “Airplane Flight Cycles at time of SB release.” While the service bulletin refers to the flight cycles accumulated on the airplane at the “time of SB release,” this AD specifies the flight cycles accumulated on the airplane “as of the effective date of this AD.”

(2) Where paragraph 1.E., “Compliance,” of the service bulletin specifies “Initial Inspection Threshold From SB Rel Upper and Lower Skin,” this AD requires compliance within the specified compliance times after the effective date of this AD.

(3) Where paragraph 1.E., “Compliance,” of the service bulletin specifies “Repeat every * * *,” this AD requires compliance at intervals not to exceed the specified flight cycles or years.

No Reporting

(g) Although Boeing Alert Service Bulletin 727-53A0223, dated March 28, 2002, specifies to submit information to the manufacturer, this AD does not include that requirement.

Alternative Methods of Compliance (AMOCs)

(h)(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. Send information to ATTN: Berhane Alazar, Aerospace Engineer, Airframe Branch, ANM-120S, FAA, Seattle Aircraft Certification Office, 1601 Lind Avenue, SW., Renton, Washington 98057-3356; telephone (425) 917-6577; fax (425) 917-6590.

(2) To request a different method of compliance or a different compliance time for this AD, follow the procedures in 14 CFR 39.19. Before using any approved AMOC on any airplane to which the AMOC applies, notify your principal maintenance inspector (PMI) or principal avionics inspector (PAI), as appropriate, in the FAA Flight Standards District Office (FSDO), or lacking a principal inspector, your local FSDO. The AMOC Start Printed Page 12243approval letter must specifically reference this AD.

(3) An AMOC that provides an acceptable level of safety may be used for any repair required by this AD, if it is approved by an Authorized Representative for the Boeing Commercial Airplanes Delegation Option Authorization Organization who 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.

Material Incorporated by Reference

(i) You must use Boeing Alert Service Bulletin 727-53A0223, dated March 28, 2002, to do the actions required by this AD, unless the AD specifies otherwise.

(1) The Director of the Federal Register approved the incorporation by reference of this service information under 5 U.S.C. 552(a) and 1 CFR part 51.

(2) For service information identified in this AD, contact Boeing 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.

(3) You may review copies of the 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 or 425-227-1152.

(4) You may also review copies of the 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/​code_​of_​federal_​regulations/​ibr_​locations.html.

Start Signature

Issued in Renton, Washington, on February 27, 2009.

Ali Bahrami,

Manager, Transport Airplane Directorate, Aircraft Certification Service.

End Signature End Supplemental Information

[FR Doc. E9-5957 Filed 3-23-09; 8:45 am]

BILLING CODE 4910-13-P