Document ID: FAA-2017-0499-0001
Agency: faa
Document Type: Proposed Rule
Title: Airworthiness Directives: The Boeing Company Airplanes
Posted Date: 2017-05-30T04:00Z

[Federal Register Volume 82, Number 102 (Tuesday, May 30, 2017)]
[Proposed Rules]
[Pages 24595-24597]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2017-10606]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2017-0499; Directorate Identifier 2016-NM-205-AD]
RIN 2120-AA64

Airworthiness Directives; The Boeing Company Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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SUMMARY: We propose to adopt a new airworthiness directive (AD) for 
certain The Boeing Company Model 747-400, 747-400F, and 747-8F series 
airplanes. This proposed AD was prompted by reports of failure of the 
fastener assemblies on the crew access ladder handrails. This proposed 
AD would require replacing the fastener assemblies. We are proposing 
this AD to address the unsafe condition on these products.

DATES: We must receive comments on this proposed AD by July 14, 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: 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: Contractual & Data Services (C&DS), 
2600 Westminster Blvd., MC 110-SK57, Seal Beach, CA 90740-5600; 
telephone 562-797-1717; 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-2017-0499.

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-
0499; 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

[[Page 24596]]

available in the AD docket shortly after receipt.

FOR FURTHER INFORMATION CONTACT: Susan L. Monroe, Aerospace Engineer, 
Cabin Safety and Environmental Systems Branch, ANM-150S, FAA, Seattle 
Aircraft Certification Office (ACO), 1601 Lind Avenue SW., Renton, WA; 
phone: 425-917-6457; fax: 425-917-6590; email: susan.l.monroe@faa.gov.

SUPPLEMENTARY INFORMATION:

Comments Invited

    We invite you to send any written relevant data, views, or 
arguments about this proposed AD. Send your comments to an address 
listed under the ADDRESSES section. Include ``Docket No. FAA-2017-0499; 
Directorate Identifier 2016-NM-205-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 reports of failure of the fastener assemblies on 
the crew access ladder handrails. Bolts on existing fastener assemblies 
for the crew ladder handrail are too short to ensure self-locking nut 
elements are fully engaged. This condition, if not corrected, could 
result in the fastener assemblies on the crew access ladder handrails 
coming loose, which could result in serious or fatal injury to 
personnel.

Related Service Information Under 1 CFR Part 51

    We reviewed Boeing Special Attention Service Bulletin 747-25-3693, 
dated November 10, 2016. The service information describes procedures 
for replacing the existing fastener assemblies with new assemblies on 
the crew access ladder handrails. 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, see this service 
information at http://www.regulations.gov by searching for and locating 
Docket No. FAA-2017-0499.

Differences Between This Proposed AD and the Service Information

    Boeing Special Attention Service Bulletin, 747-25-3693, dated 
November 10, 2016, applies to certain The Boeing Company Model 747-400, 
747-400F, and 747-8F series airplanes. This proposed AD would apply to 
those airplanes and all Model 747-8F airplanes with an original 
certificate of airworthiness, or an original export certificate of 
airworthiness, issued after November 10, 2016. Because the affected 
parts are rotable parts, we have determined that these parts could 
later be installed on airplanes that were initially delivered with 
acceptable parts, thereby subjecting those airplanes to the unsafe 
condition. We have coordinated this difference with Boeing.

Costs of Compliance

    We estimate that this proposed AD affects 84 airplanes of U.S. 
registry. We estimate the following costs to comply with this proposed 
AD:

                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
                                                                                     Cost per      Cost on U.S.
               Action                         Labor cost            Parts cost        product        operators
----------------------------------------------------------------------------------------------------------------
Replacement........................  3 work-hours x $85 per hour          $2,418          $2,673        $224,532
                                      = $255.
----------------------------------------------------------------------------------------------------------------

    According to the manufacturer, some of the costs of this proposed 
AD may be covered under warranty, thereby reducing the cost impact on 
affected individuals. We do not control warranty coverage for affected 
individuals. As a result, we have included all costs in our cost 
estimate.

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.

[[Page 24597]]

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

0
1. The authority citation for part 39 continues to read as follows:

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

Sec.  39.13   [Amended]

0
2. The FAA amends Sec.  39.13 by adding the following new airworthiness 
directive (AD):

The Boeing Company: Docket No. FAA-2017-0499; Directorate Identifier 
2016-NM-205-AD.

(a) Comments Due Date

    We must receive comments by July 14, 2017.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to The Boeing Company airplanes identified in 
paragraphs (c)(1), (c)(2), and (c)(3) of this AD, certificated in 
any category.
    (1) Model 747-400, 747-400F, and 747-8F series airplanes, as 
identified in Boeing Special Attention Service Bulletin 747-25-3693, 
dated November 10, 2016.
    (2) Model 747-8F series airplanes with an original certificate 
of airworthiness, or an original export certificate of 
airworthiness, issued after November 10, 2016, and before the 
effective date of this AD.
    (3) Model 747-8F series airplanes with an original certificate 
of airworthiness, or an original export certificate of 
airworthiness, issued on or after the effective date of this AD.

(d) Subject

    Air Transport Association (ATA) of America Code 25; Equipment/
furnishings.

(e) Unsafe Condition

    This AD was prompted by reports of failure of the fastener 
assemblies on the crew access ladder handrails. We are issuing this 
AD to prevent the fastener assemblies from coming loose on the crew 
access ladder handrails, which could result in serious or fatal 
injury to personnel.

(f) Compliance

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

(g) Replacement

    For airplanes identified in paragraph (c)(1) of this AD: Within 
36 months after the effective date of this AD, replace the fastener 
assemblies in the crew access ladder handrails with new fastener 
assemblies, in accordance with the Accomplishment Instructions of 
Boeing Special Attention Service Bulletin 747-25-3693, dated 
November 10, 2016.

(h) Inspection and Replacement

    (1) For airplanes identified in paragraph (c)(2) of this AD: 
Within 36 months after the effective date of this AD, do a general 
visual inspection of the crew access ladder handrails for the 
discrepant fastener assembly hardware identified in the 
Accomplishment Instructions of Boeing Special Attention Service 
Bulletin 747-25-3693, dated November 10, 2016. A review of airplane 
maintenance records is acceptable in lieu of this inspection, if the 
part number(s) of the fastener assembly hardware can be conclusively 
determined from that review.
    (2) If any discrepant fastener assembly hardware is found, 
within 36 months after the effective date of this AD, replace the 
discrepant fastener assemblies in the crew access ladder handrails 
with new fastener assemblies, in accordance with the Accomplishment 
Instructions of Boeing Special Attention Service Bulletin 747-25-
3693, dated November 10, 2016.

(i) Parts Installation Limitation

    For airplanes identified in paragraphs (c)(1), (c)(2), and 
(c)(3) of this AD: As of the effective date of this AD, no person 
may install the discrepant fastener hardware identified in the 
Accomplishment Instructions of Boeing Special Attention Service 
Bulletin 747-25-3693, dated November 10, 2016, on a crew access 
ladder on any airplane.

(j) Alternative Methods of Compliance (AMOCs)

    (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. 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 (k)(1) of this AD. 
Information may be emailed to: 9-ANM-Seattle-ACO-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, Seattle 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 
(j)(4)(i) and (j)(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.

(k) Related Information

    (1) For more information about this AD, contact Susan L. Monroe, 
Aerospace Engineer, Cabin Safety and Environmental Systems Branch, 
ANM-150S, FAA, Seattle ACO, 1601 Lind Avenue SW., Renton, WA; phone: 
425-917-6457; fax: 425-917-6590; email: susan.l.monroe@faa.gov.
    (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-
5600; telephone 562-797-1717; 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 May 17, 2017.
Michael Kaszycki,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2017-10606 Filed 5-26-17; 8:45 am]
 BILLING CODE 4910-13-P