05-20075. Airworthiness Directives; Boeing Model 727, 727C, 727-100, and 727-100C Series Airplanes

AGENCY:

Federal Aviation Administration, DOT.

ACTION:

Final rule.

SUMMARY:

This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 727, 727C, 727-100, and 727-100C series airplanes. This AD requires repetitive inspections of the frame inner chord, outer chord, and web of the forward and aft edge frames of the lower lobe forward cargo door (FCD) cutout, and corrective action if necessary. The actions specified by this AD are intended to detect and correct fatigue cracking of the forward and aft edge frames of the lower lobe FCD cutout, which could result in the loss of the FCD and rapid decompression of the airplane. This action is intended to address the identified unsafe condition.

DATES:

Effective November 16, 2005.

The incorporation by reference of a certain publication listed in the regulations is approved by the Director of the Federal Register as of November 16, 2005.

ADDRESSES:

The service information referenced in this AD may be obtained from Boeing Commercial Airplanes, P.O. Box 3707, Seattle, Washington 98124-2207. This information may be examined at the Federal Aviation Administration (FAA), Transport Airplane Directorate, Rules Docket, 1601 Lind Avenue, SW., Renton, Washington.

FOR FURTHER INFORMATION CONTACT:

Daniel F. Kutz, Aerospace Engineer, Airframe Branch, ANM-120S, FAA, Seattle Aircraft Certification Office, 1601 Lind Avenue, SW., Renton, Washington 98055-4056; telephone [phone]; fax [phone].

SUPPLEMENTARY INFORMATION:

A proposal to amend part 39 of the Federal Aviation Regulations (14 CFR part 39) to include an airworthiness directive (AD) that is applicable to certain Boeing Model 727, 727C, 727-100, and 727-100C series airplanes was published as a supplemental notice of proposed rulemaking (NPRM) in the Federal Register on August 22, 2005 (70 FR 48904). That action proposed to require repetitive inspections of the frame inner chord, outer chord, and web of the forward and aft edge frames of the lower lobe forward cargo door cutout, and corrective action if necessary.

Clarification of Alternative Method of Compliance (AMOC) Paragraph

We have revised this action to clarify the appropriate procedure for notifying the principal inspector before using any approved AMOC on any airplane to which the AMOC applies.

Comments

We provided the public the opportunity to participate in the development of this AD. We have considered the comment received. The commenter supports the supplemental NPRM.

Conclusion

We have carefully reviewed the available data, including the comments received, and determined that air safety and the public interest require adopting the AD with the changes described previously. We have determined that these changes will neither increase the economic burden on any operator nor increase the scope of the AD.

Interim Action

We consider this final rule to be an interim action. The manufacturer is currently developing a modification that will address the unsafe condition identified in this AD. Once this modification is developed, approved, and available, we may consider additional rulemaking.

Cost Impact

There are approximately 211 airplanes of the affected design in the worldwide fleet. The FAA estimates that 116 airplanes of U.S. registry will be affected by this AD, that it will take approximately 6 to 8 work hours per airplane to accomplish the required inspections, and that the average labor rate is $65 per work hour. Based on these figures, the cost impact of the AD on U.S. operators is estimated to be between $45,240 and $60,320, or between $390 and $520 per airplane.

The cost impact figure discussed above is based on assumptions that no operator has yet accomplished any of the requirements of this AD action, and that no operator would accomplish those actions in the future if this AD were not adopted. The cost impact figures discussed in AD rulemaking actions represent only the time necessary to perform the specific actions actually required by the AD. These figures typically do not include incidental costs, such as the time required to gain access and close up, planning time, or time necessitated by other administrative actions.

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 Impact

The regulations adopted herein 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. Therefore, it is determined that this final rule does not have federalism implications under Executive Order 13132.

For the reasons discussed above, I certify that this action (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. A final evaluation has been prepared for this action and it is contained in the Rules Docket. A copy of it may be obtained from the Rules Docket at the location provided under the caption ADDRESSES.

List of Subjects in 14 CFR Part 39

• Air transportation
• Aircraft
• Aviation safety
• Incorporation by reference
• Safety

Adoption of the Amendment

Accordingly, pursuant to the authority delegated to me by the Administrator, the Federal Aviation Administration amends part 39 of the Federal Aviation Regulations (14 CFR part 39) as follows:

PART 39—AIRWORTHINESS DIRECTIVES

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

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

§ 39.13

[Amended]

2. Section 39.13 is amended by adding the following new airworthiness directive:

2005-20-33 Boeing: Amendment 39-14330. Docket 2003-NM-238-AD.

Applicability: Model 727, 727C, 727-100, and 727-100C series airplanes, line numbers 1 through 694 inclusive; certificated in any category.

Compliance: Required as indicated, unless accomplished previously.

To detect and correct fatigue cracking of the forward and aft edge frames of the lower lobe forward cargo door (FCD) cutout, which could result in the loss of the FCD and rapid decompression of the airplane, accomplish the following:

Note 1:

This AD is related to AD 98-11-03 R1, amendment 39-10983, and affects Structural Significant Item (SSI) F-11B of the Boeing 727 Supplemental Structural Inspection Document (SSID) program, D6-48040-1, Revision H, dated June 1994.

Initial and Repetitive Inspections

(a) For airplanes on which the forward and aft edge frames of the lower lobe FCD cutout have not been inspected per AD 98-11-03 R1 as of the effective date of this AD: Prior to the accumulation of 21,000 total flight cycles, or within 3,000 flight cycles after the effective date of this AD, whichever occurs later, do the inspections specified in paragraph (c) of this AD.

(b) For airplanes on which the forward and aft edge frames of the lower lobe FCD cutout have been inspected per AD 98-11-03 R1 as of the effective date of this AD: Within the next scheduled inspection required by AD 98-11-03 R1, or within 3,000 flight cycles after the effective date of this AD, whichever occurs first, do the inspections specified in paragraph (c) of this AD.

(c) At the time specified in paragraph (a) or paragraph (b) of this AD, as applicable: Perform the detailed and high frequency eddy current inspections for cracks in the web and the inner and outer chords of the forward and aft frames of the forward cargo doorway in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 727-53A0229, dated March 24, 2005. Repeat the inspections thereafter at intervals not to exceed 3,000 flight cycles.

Corrective Action

(d) If any crack is found during any inspection required by paragraph (c) of this AD: Before further flight, repair per a method approved by the Manager, Seattle Aircraft Certification Office (ACO), FAA; or according to data meeting the certification basis of the airplane 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 approval must meet the certification basis of the airplane, and the approval must specifically reference this AD.

Certain Actions Constitute Compliance With AD 98-11-03 R1

(e) Accomplishment of the inspections specified in paragraph (c) of this AD is terminating action for the inspections required by AD 98-11-03 R1 that pertain to SSI F-11B of Boeing Document D6-48040-1, Boeing 727 SSID, Revision H, dated June 1994, for the areas specified in paragraph (c) of this AD only. Accomplishment of the actions required by paragraph (c) of this AD does not terminate the inspections required by AD 98-11-03 R1 for the remaining areas of SSI F-11B and does not terminate the remaining requirements of AD 98-11-03 R1.

No Reporting Required

(f) Although the service bulletin referenced in this AD specifies to provide certain information to the manufacturer, this AD does not include that requirement.

Alternative Methods of Compliance

(g)(1) In accordance with 14 CFR 39.19, the Manager, Seattle ACO, is authorized to approve alternative methods of compliance (AMOCs) for this AD.

(2) Before using any AMOC approved in accordance with § 39.19 on any airplane to which the AMOC applies, notify the appropriate principal inspector in the FAA Flight Standards Certificate Holding District Office.

Incorporation by Reference

(h) Unless otherwise specified in this AD, the actions must be done in accordance with Boeing Alert Service Bulletin 727-53A0229, dated March 24, 2005. This incorporation by reference was approved by the Director of the Federal Register in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. To get copies of this service information, contact Boeing Commercial Airplanes, P.O. Box 3707, Seattle, Washington 98124-2207. To inspect copies of this service information, go to the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington; or to the National Archives and Records Administration (NARA). For information on the availability of this material at the NARA, call [phone], or go to http://www.archives.gov/​federal_​register/​code_​of_​federal_​regulations/​ibr_​locations.html.

Effective Date

(i) This amendment becomes effective on November 16, 2005.

Issued in Renton, Washington, on September 29, 2005.

Ali Bahrami,

Manager, Transport Airplane Directorate, Aircraft Certification Service.