2017-15554. Airworthiness Directives; The Boeing Company Airplanes

AGENCY:

Federal Aviation Administration (FAA), DOT.

ACTION:

Notice of proposed rulemaking (NPRM).

SUMMARY:

We propose to adopt a new airworthiness directive (AD) for certain The Boeing Company Model 757-200, -200CB, and -300 series airplanes. This proposed AD was prompted by a report of fatigue cracking found in a certain fuselage frame, which severed the inner chord and web. This proposed AD would require inspecting the fuselage frame for existing repairs, repetitive inspections, and applicable repairs. We are proposing this AD to address the unsafe condition on these products.

DATES:

We must receive comments on this proposed AD by September 11, 2017.

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: [phone].
• 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: Contractual & Data Services (C&DS), 2600 Westminster Blvd., MC 110-SK57, Seal Beach, CA 90740; telephone: [phone]; 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. It is also available on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2017-0711.

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-2017-0711; 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 NPRM, the regulatory evaluation, any comments received, and other information. The street address for the Docket Office (phone: [phone]) is in the ADDRESSES section. Comments will be available in the AD docket shortly after receipt.

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: [phone]; fax: [phone]; email: [e-mail].

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-2017-0711; Directorate Identifier 2017-NM-001-AD” at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of this NPRM. We will consider all comments received by the closing date and may amend this NPRM 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 NPRM.

Discussion

We have received a report of a crack in the fuselage frame at station (STA) 1640, at stringer (S) 14-R, adjacent to door stop number 5. The inner chord and web of the STA 1640 fuselage frame had been severed after developing a crack. Analysis revealed that the crack was caused by fatigue due to flight loads and pressurization of the fuselage. Cracking of the fuselage frame, if not detected and corrected, could result in reduced structural integrity of the airplane.

Related Service Information Under 1 CFR Part 51

We reviewed Boeing Alert Service Bulletin 757-53A0108, dated November 14, 2016. The service information describes procedures for an inspection of the fuselage frame for existing frame repairs, repetitive high frequency eddy current and low frequency eddy current inspections for cracking in specified areas with no existing frame repair, and repair of any cracking.

We also reviewed Aviation Partners Boeing (APB) Alert Service Bulletin AP757-53-001, Revision 1, dated June 21, 2017. The service information provides compliance times for accomplishing the procedures identified in Boeing Alert Service Bulletin 757-53A0108, dated November 14, 2016; for airplanes on which APB blended or scimitar blended winglets are installed.

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 accomplishment of the actions identified as “RC” (required for compliance) in the Accomplishment Instructions of Boeing Alert Service Bulletin 757-53A0108, dated November 14, 2016, described previously, except for differences between this proposed AD and the service information that are identified in the regulatory text of this proposed AD.

For information on the procedures and compliance times, see this Boeing service information at http://www.regulations.gov by searching for and locating Docket No. FAA-2017-0711, except for airplanes on which blended or scimitar blended winglets are installed in accordance with Supplemental Type Certificate ST01518SE, which have different repetitive compliance times as specified in APB Alert Service Bulletin AP757-53-001, Revision 1, dated June 21, 2017.

For airplanes on which blended or scimitar blended winglets are installed in accordance with Supplemental Type Certificate ST01518SE, the repetitive compliance times have a range, depending on airplane configuration. The earliest repetitive interval is 1,950 flight cycles; the latest repetitive interval is 8,600 flight cycles.

Costs of Compliance

We estimate that this proposed AD affects 606 airplanes of U.S. registry. We estimate the following costs to comply with this proposed AD:

Estimated Costs

Action	Labor cost	Parts cost	Cost per product	Cost on U.S. operators
Inspect for existing frame repairs	1 work-hour × $85 per hour = $85	$0	$85	$51,510.
Repetitive high and low frequency inspections for Groups 1 through 3 airplanes (598 airplanes)	48 work-hours × $85 per hour = $4,080 per inspection cycle	0	4,080	$2,439,840 per inspection cycle.
Repetitive high and low frequency inspections for Groups 4 and 5 airplanes (8 airplanes)	26 work-hours × $85 per hour = $2,210 per inspection cycle	0	2,210	$17,680 per inspection cycle.

We have received no definitive data that would enable us to provide cost estimates for the on-condition repair specified in this proposed AD.

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.

List of Subjects in 14 CFR Part 39

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

The Proposed Amendment

Accordingly, under the authority delegated to me by the Administrator, the FAA proposes to amend 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. The FAA amends § 39.13 by adding the following new airworthiness directive (AD):

The Boeing Company: Docket No. FAA-2017-0711; Directorate Identifier 2017-NM-003-AD.

(a) Comments Due Date

We must receive comments by September 11, 2017.

(b) Affected ADs

None.

(c) Applicability

This AD applies to The Boeing Company Model 757-200, -200CB, and -300 series airplanes, certificated in any category, as identified in Boeing Alert Service Bulletin 757-53A0108, dated November 14, 2016.

(d) Subject

Air Transport Association (ATA) of America Code 53; Fuselage.

(e) Unsafe Condition

This AD was prompted by a report of fatigue cracking found in the fuselage frame at station (STA) 1640, which severed the inner chord and web. We are issuing this AD to detect and correct cracking of the fuselage frame at STA 1640, which could result in reduced structural integrity of the airplane.

(f) Compliance

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

(g) Actions Required for Compliance

(1) For all airplanes except those identified in paragraph (g)(2) of this AD: Do all applicable actions identified as “RC” (required for compliance) in, and in accordance with, the Accomplishment Instructions of Boeing Alert Service Bulletin 757-53A0108, dated November 14, 2016; except as provided by paragraph (h)(1) of this AD. Do the actions at the applicable times specified in paragraph 1.E., “Compliance,” of Boeing Alert Service 757-53A0108, dated November 14, 2016, except as provided by paragraph (h)(2) of this AD.

(2) For airplanes on which blended or scimitar blended winglets are installed in accordance with Supplemental Type Certificate ST01518SE: Do all applicable actions identified as “RC” (required for compliance) in, and in accordance with, the Accomplishment Instructions of APB Alert Service Bulletin AP757-53-001, Revision 1, dated June 21, 2017; and Boeing Alert Service Bulletin 757-53A0108, dated November 14, 2016; except as provided by paragraph (h)(1) of this AD. Do the actions at the applicable times specified in paragraph 1.E., “Compliance,” of Aviation Partners Boeing (APB) Alert Service Bulletin AP757-53-001, Revision 1, dated June 21, 2017, except as provided by paragraph (h)(2) of this AD.

(h) Exceptions to Service Information Specifications

(1) Where Boeing Alert Service Bulletin 757-53A0108, dated November 14, 2016, specifies contacting Boeing for instructions, and specifies that action as RC: This AD requires using a method approved in accordance with the procedures specified in paragraph (i) of this AD.

(2) Where Boeing Alert Service Bulletin 757-53A0108, dated November 14, 2016, and APB Alert Service Bulletin AP757-53-001, Revision 1, dated June 21, 2017, use the phrase “after the original issue of this service bulletin” for determining compliance, this AD requires compliance within the specified compliance time after the effective date of this AD.

(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 [e-mail].

(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) Except as required by paragraph (h)(1) of this AD: For service information that contains steps that are labeled as RC, the provisions of paragraphs (i)(4)(i) and (i)(4)(ii) of this AD apply.

(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: [phone]; fax: [phone]; email: [e-mail].

(2) For service information identified in this AD, contact Boeing Commercial Airplanes, Attention: Contractual & Data Services (C&DS), 2600 Westminster Blvd., MC 110-SK57, Seal Beach, CA 90740; telephone: [phone]; 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.

Issued in Renton, Washington, on July 18, 2017.

Victor Wicklund,

Acting Manager, Transport Airplane Directorate, Aircraft Certification Service.