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Proposed Rule

Airworthiness Directives; The Boeing Company Airplanes

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Start Preamble

AGENCY:

Federal Aviation Administration (FAA), DOT.

ACTION:

Notice of proposed rulemaking (NPRM).

SUMMARY:

We propose to adopt a new airworthiness directive (AD) for all The Boeing Company Model 727 airplanes. This proposed AD was prompted by analysis of the cam support assemblies of the main cargo door that indicated the repetitive high frequency eddy current (HFEC) inspections required by the existing maintenance program are not adequate to detect cracks before two adjacent cam support assemblies of the main cargo door could fail. This proposed AD would require repetitive ultrasonic inspections for cracking of the cam support assemblies of the main cargo door and replacement if necessary. We are proposing this AD to detect and correct cracking of the cam support assemblies of the main cargo door. Such cracking could result in reduced structural integrity of the main cargo door and consequent rapid decompression of the airplane.

DATES:

We must receive comments on this proposed AD by November 18, 2016.

ADDRESSES:

You may send comments, using the procedures found in 14 CFR 11.43 and 11.45, by any of the following methods:

  • Federal eRulemaking Portal: Go to http://www.regulations.gov. Follow the instructions for submitting comments.
  • Fax: 202-493-2251.
  • Mail: U.S. Department of Transportation, Docket Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New Jersey Avenue SE., Washington, DC 20590.
  • Hand Delivery: Deliver to Mail address above between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays.

For service information identified in this NPRM, contact Boeing Commercial Airplanes, Attention: Data & Services Management, P.O. Box 3707, MC 2H-65, Seattle, WA 98124-2207; telephone: 206-544-5000, extension 1; fax: 206-766-5680; Internet: https://www.myboeingfleet.com. You may view Start Printed Page 68374this referenced service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For information on the availability of this material at the FAA, call 425-227-1221. It is also available on the internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2016-9184.

Examining the AD Docket

You may examine the AD docket on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2016-9184; 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 proposed AD, the regulatory evaluation, any comments received, and other information. The street address for the Docket Office (phone: 800-647-5527) is in the ADDRESSES section. Comments will be available in the AD docket shortly after receipt.

Start Further Info

FOR FURTHER INFORMATION CONTACT:

Chandra Ramdoss, Aerospace Engineer, Airframe Branch, ANM-120L, FAA, Los Angeles Aircraft Certification Office (ACO), 3960 Paramount Boulevard, Lakewood, CA 90712-4137; phone: 562-627-5239; fax: 562-627-5210; email: chandraduth.ramdoss@faa.gov.

End Further Info End Preamble Start Supplemental Information

SUPPLEMENTARY INFORMATION:

Comments Invited

We invite you to send any written relevant data, views, or arguments about this proposal. Send your comments to an address listed under the ADDRESSES section. Include “Docket No. FAA-2016-9184; Directorate Identifier 2016-NM-060-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 will post all comments we receive, without change, to http://www.regulations.gov, including any personal information you provide. We will also post a report summarizing each substantive verbal contact we receive about this proposed AD.

Discussion

We have received a report indicating that the analysis of the cam support assemblies of the main cargo door, having part numbers 69-23588-5 and 69-23588-6, indicated that the repetitive HFEC inspections required by the existing maintenance program are not adequate to detect cracks before two adjacent cam support assemblies of the main cargo door could fail. This condition, if not corrected, could result in reduced structural integrity of the main cargo door and consequent rapid decompression of the airplane.

Related Service Information Under 1 CFR Part 51

We reviewed Boeing Alert Service Bulletin 727-52A0151, dated February 12, 2016. The service information describes procedures for an ultrasonic inspection of the cam support assemblies of the main cargo door for cracking, and replacement if necessary. This service information is reasonably available because the interested parties have access to it through their normal course of business or by the means identified in the ADDRESSES section.

FAA's Determination

We are proposing this AD because we evaluated all the relevant information and determined the unsafe condition described previously is likely to exist or develop in other products of the same type design.

Proposed AD Requirements

This proposed AD would require accomplishing the actions specified in the service information described previously, except as discussed under “Differences Between this Proposed AD and the Service Information.” For information on the procedures and compliance times, see this service information at http://www.regulations.gov by searching for and locating Docket No. FAA-2016-9184.

Differences Between This Proposed AD and the Service Information

Boeing Alert Service Bulletin 727-52A0151, dated February 12, 2016, only affects Model 727C, 727-100C, and 727-200F series airplanes. The applicability of this proposed AD extends to all Model 727 airplanes. Boeing Alert Service Bulletin 727-52A0151, dated February 12, 2016, only affects certain part numbers. We are extending the list of affected part numbers to include 69-23588-1 and 69-23588-2, which were not referenced in Boeing Alert Service Bulletin 727-52A0151, dated February 12, 2016. These differences exist to ensure all affected parts are inspected in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 727-52A0151, dated February 12, 2016. For all airplanes affected by this AD, including airplanes not listed in the effectivity of Boeing Alert Service Bulletin 727-52A0151, dated February 12, 2016, compliance with paragraph (h) of this AD must be done using Boeing Alert Service Bulletin 727-52A0151, dated February 12, 2016. Therefore, an alternative method of compliance (AMOC) approval is not necessary for those airplanes if Boeing Alert Service Bulletin 727-52A0151, dated February 12, 2016, is used. This difference has been coordinated with Boeing.

Costs of Compliance

We estimate that this proposed AD affects 45 airplanes of U.S. registry. We estimate the following costs to comply with this proposed AD:

Estimated Costs

ActionLabor costParts costCost per productCost on U.S. operators
Inspection6 work-hours × $85 per hour = $510 per inspection cycle$0$510 per inspection cycle$22,950 per inspection cycle.

We estimate the following costs to do any necessary replacements that would be required based on the results of the proposed inspection. We have no way of determining the number of aircraft that might need this replacement:Start Printed Page 68375

On-Condition Costs

ActionLabor costParts costCost per product
Replacement60 work-hours × $85 per hour = $5,100$14,107$19,207

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

We determined that this proposed AD would not have federalism implications under Executive Order 13132. This proposed AD would 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 this proposed regulation:

(1) Is not a “significant regulatory action” under Executive Order 12866,

(2) Is not a “significant rule” under the DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979),

(3) Will not affect intrastate aviation in Alaska, and

(4) 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.

Start List of Subjects

List of Subjects in 14 CFR Part 39

  • Air transportation
  • Aircraft
  • Aviation safety
  • Incorporation by reference
  • Safety
End List of Subjects

The Proposed Amendment

Accordingly, under the authority delegated to me by the Administrator, the FAA proposes to amend 14 CFR part 39 as follows:

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 airworthiness directive (AD):

End Amendment Part

The Boeing Company: Docket No. FAA-2016-9184; Directorate Identifier 2016-NM-060-AD.

(a) Comments Due Date

We must receive comments by November 18, 2016.

(b) Affected ADs

None.

(c) Applicability

This AD applies to all The Boeing Company Model 727, 727C, 727-100, 727-100C, 727-200, and 727-200F series airplanes, certificated in any category,

(d) Subject

Air Transport Association (ATA) of America Code 52, Doors.

(e) Unsafe Condition

This AD was prompted by analysis of the cam support assemblies of the main cargo door that indicated the repetitive high frequency eddy current (HFEC) inspection required by the existing maintenance program are not adequate to detect cracks before two adjacent cam support assemblies of the main cargo door could fail. We are issuing this AD to detect and correct cracking of the cam support assemblies of the main cargo door. Such cracking could result in reduced structural integrity of the main cargo door and consequent rapid decompression of the airplane.

(f) Compliance

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

(g) Inspection To Determine Part Numbers

At the later of the times specified in paragraphs (g)(1) and (g)(2) of this AD: Inspect the cam support assemblies of the main cargo door to determine whether part number (P/N) 69-23588-1, 69-23588-2, 69-23588-5, 69-23588-6, 69-23588-9, or 69-23588-10 is installed. A review of airplane maintenance records is acceptable in lieu of this inspection if the part number(s) of the cam support assemblies of the main cargo door can be conclusively determined from that review.

(1) Before the accumulation of 18,000 total flight cycles.

(2) Within 1,771 flight cycles or 27 months after the effective date of this AD, whichever occurs later.

(h) Repetitive Inspections of the Cam Support Assemblies of the Main Cargo Door and Corrective Actions

If, during any inspection required by paragraph (g) of this AD, any cam support assembly of the main cargo door having P/N 69-23588-1, 69-23588-2, 69-23588-5, 69-23588-6, 69-23588-9, or 69-23588-10 is determined to be installed: At the later of the times specified in paragraphs (g)(1) and (g)(2) of this AD, do an ultrasonic inspection to detect cracking of the affected cam support assemblies of the main cargo door; and do all applicable replacements; in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 727-52A0151, dated February 12, 2016. Do all applicable replacements before further flight. Repeat the inspections thereafter at the applicable time specified in paragraph 1.E., “Compliance,” of Boeing Alert Service Bulletin 727-52A0151, dated February 12, 2016.

(i) Alternative Methods of Compliance (AMOCs)

(1) The Manager, Los Angeles 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 CFR 39.19, send your request to your principal inspector or local 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 paragraph (j)(1) of this AD. Information may be emailed to: 9-ANM-LAACO-AMOC-Requests@faa.gov.

(2) Before using any approved AMOC, notify your appropriate principal inspector, or lacking a principal inspector, the manager of the local flight standards district office/certificate holding district office.

(3) An AMOC that provides an acceptable level of safety may be used for any repair, modification, or alteration required by this AD if it is approved by the Boeing Commercial Airplanes Organization Designation Authorization (ODA) that has been authorized by the Manager, Los Angeles ACO, to make those findings. To be approved, the repair method, modification deviation, or alteration deviation must meet the certification basis of the airplane, and the approval must specifically refer to this AD.

(4) For service information that contains steps that are labeled as Required for Compliance (RC), the provisions of paragraphs (i)(4)(i) and (i)(4)(ii) of this AD apply.Start Printed Page 68376

(i) The steps labeled as RC, including substeps under an RC step and any figures identified in an RC step, must be done to comply with the AD. If a step or substep is labeled “RC Exempt,” then the RC requirement is removed from that step or substep. An AMOC is required for any deviations to RC steps, including substeps and identified figures.

(ii) Steps not labeled as RC may be deviated from using accepted methods in accordance with the operator's maintenance or inspection program without obtaining approval of an AMOC, provided the RC steps, including substeps and identified figures, can still be done as specified, and the airplane can be put back in an airworthy condition.

(j) Related Information

(1) For more information about this AD, contact Chandra Ramdoss, Aerospace Engineer, Airframe Branch, ANM-120L, FAA, Los Angeles ACO, 3960 Paramount Boulevard, Lakewood, CA 90712-4137; phone: 562-627-5239; fax: 562-627-5210; email: chandraduth.ramdoss@faa.gov.

(2) For service information identified in this AD, contact Boeing Commercial Airplanes, Attention: Data & Services Management, P.O. Box 3707, MC 2H-65, Seattle, WA 98124-2207; telephone: 206-544-5000, extension 1; fax: 206-766-5680; Internet: https://www.myboeingfleet.com. You may view this referenced service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For information on the availability of this material at the FAA, call 425-227-1221.

Start Signature

Issued in Renton, Washington, on September 27, 2016.

Dionne Palermo,

Acting Manager, Transport Airplane Directorate, Aircraft Certification Service.

End Signature End Supplemental Information

[FR Doc. 2016-23938 Filed 10-3-16; 8:45 am]

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