[Federal Register Volume 83, Number 234 (Thursday, December 6, 2018)]
[Proposed Rules]
[Pages 62741-62743]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2018-26361]



[[Page 62741]]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2018-1004; Product Identifier 2018-NM-106-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 all 
The Boeing Company Model 737-100, -200, -200C, -300, -400, and -500 
series airplanes. This proposed AD was prompted by reports of cracks 
caused by corrosion of the edge of the bore of the spot face and 
corrosion of the lug bore of certain side-strut support fitting lugs. 
This proposed AD would require repetitive detailed inspections of the 
left and right side-strut support fitting lugs with bushings installed 
for any corrosion, any crack, or any severed lug; repetitive detailed 
and high frequency eddy current (HFEC) inspections of the left and 
right side-strut support fitting lugs with bushings removed for any 
corrosion or any crack; and applicable on-condition actions. We are 
proposing this AD to address the unsafe condition on these products.

DATES: We must receive comments on this proposed AD by January 22, 
2019.

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 
Standards Branch, 2200 South 216th St., Des Moines, WA. For information 
on the availability of this material at the FAA, call 206-231-3195. It 
is also available on the internet at http://www.regulations.gov by 
searching for and locating Docket No. FAA-2018-1004.

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-2018-
1004; or in person at Docket Operations 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 Docket Operations (phone: 800-647-
5527) is in the ADDRESSES section. Comments will be available in the AD 
docket shortly after receipt.

FOR FURTHER INFORMATION CONTACT: Alan Pohl, Aerospace Engineer, 
Airframe Section, FAA, Seattle ACO Branch, 2200 South 216th St., Des 
Moines, WA 98198; phone and fax: 206-231-3527; email: 
[email protected].

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-2018-1004; 
Product Identifier 2018-NM-106-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 proposed AD.

Discussion

    We have received reports of cracks caused by corrosion of the edge 
of the bore of the spot face and corrosion of the lug bore of the body 
station (BS) 685 side-strut support fitting lugs. This condition, if 
not addressed, could result in sudden loss of the side-strut support 
fitting joint and main landing gear attachment to the airplane, 
resulting in the collapse of a main landing gear.

Related Service Information Under 1 CFR Part 51

    We reviewed Boeing Service Bulletin 737-53-1246, Revision 1, dated 
May 30, 2018. This service information describes procedures for 
repetitive detailed inspections of the left and right side-strut 
support fitting lugs at BS 685 with bushings installed for any 
corrosion, any crack, or any severed lug; repetitive detailed and HFEC 
inspections of the left and right side-strut support fitting lugs at BS 
685 with bushings removed for any corrosion or any crack; and 
applicable on-condition actions. On-condition actions include, among 
other things, inspections, corrosion removal, and a preventative 
modification. Doing the repetitive detailed and HFEC inspections of the 
side-strut support fitting lugs at BS 685 with bushings removed 
terminates the repetitive detailed inspections of the side-strut 
support fitting lugs at BS 685 with bushings 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 Service Bulletin 737-53-1246, Revision 1, dated 
May 30, 2018, described previously, except for any differences 
identified as exceptions in the regulatory text of this proposed AD.
    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-2018-1004.

Costs of Compliance

    We estimate that this proposed AD affects 302 airplanes of U.S. 
registry. We estimate the following costs to comply with this proposed 
AD:

[[Page 62742]]



                                      Estimated Costs for Required Actions
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                                                                                                 Cost on U.S.
              Action                    Labor cost        Parts cost      Cost per product        operators
----------------------------------------------------------------------------------------------------------------
Repetitive detailed inspection of  17 work-hours x $85              $0  $1,445 per           $436,390 per
 left and right side lugs with      per hour = $1,445                    inspection cycle.    inspection cycle.
 bushings installed.                per inspection
                                    cycle.
Repetitive detailed and HFEC       29 work-hours x $85               0  $2,465 per           $744,430 per
 inspections of left and right      per hour = $2,465                    inspection cycle.    inspection cycle.
 side lugs with bushings removed.   per inspection
                                    cycle.
----------------------------------------------------------------------------------------------------------------

    We estimate the following costs to do any necessary on-condition 
actions that would be required. We have no way of determining the 
number of aircraft that might need these on-condition actions:

                 Estimated Costs of On-Condition Actions
------------------------------------------------------------------------
          Labor cost                  Parts cost        Cost per product
------------------------------------------------------------------------
Up to 18 work-hour x $85 per    Unknown...............  Up to $1,530 per
 hour = $1,530 per inspection                            inspection
 cycle.                                                  cycle.
------------------------------------------------------------------------

    We have received no definitive data that would enable us to provide 
parts cost estimates for the on-condition inspections and repairs 
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.
    This proposed AD is issued in accordance with authority delegated 
by the Executive Director, Aircraft Certification Service, as 
authorized by FAA Order 8000.51C. In accordance with that order, 
issuance of ADs is normally a function of the Compliance and 
Airworthiness Division, but during this transition period, the 
Executive Director has delegated the authority to issue ADs applicable 
to transport category airplanes to the Director of the System Oversight 
Division.

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

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-2018-1004; Product Identifier 
2018-NM-106-AD.

(a) Comments Due Date

    We must receive comments by January 22, 2019.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to all The Boeing Company Model 737-100, -200, -
200C, -300, -400, and -500 series airplanes, certificated in any 
category.

(d) Subject

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

(e) Unsafe Condition

    This AD was prompted by reports of cracks caused by corrosion of 
the edge of the bore of the spot face and corrosion of the lug bore 
of the body station (BS) 685 side-strut support fitting lugs. We are 
issuing this AD to address cracks caused by corrosion, which could 
result in sudden loss of the side-strut support fitting joint and 
main landing gear attachment to the airplane, resulting in the 
collapse of a main landing gear.

(f) Compliance

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

(g) Actions for Group 7

    For airplanes identified as Group 7 in Boeing Service Bulletin 
737-53-1246, Revision 1, dated May 30, 2018: Within 120 days after 
the effective date of this AD, inspect the left and right side-strut 
support fitting lugs at BS 685 and do all applicable on-condition 
actions using a method

[[Page 62743]]

approved in accordance with the procedures specified in paragraph 
(j) of this AD.

(h) Required Actions for Groups 1 Through 6

    For airplanes identified as Groups 1 through 6 in Boeing Service 
Bulletin 737-53-1246, Revision 1, dated May 30, 2018, except as 
specified in paragraph (i) of this AD: At the applicable times 
specified in paragraph 1.E., ``Compliance,'' of Boeing Service 
Bulletin 737-53-1246, Revision 1, dated May 30, 2018, do all 
applicable actions identified as ``RC'' (required for compliance) 
in, and in accordance with, the Accomplishment Instructions of 
Boeing Service Bulletin 737-53-1246, Revision 1, dated May 30, 2018.

(i) Exceptions to Service Information Specifications

    (1) For purposes of determining compliance with the requirements 
of this AD: Where Boeing Service Bulletin 737-53-1246, Revision 1, 
dated May 30, 2018, uses the phrase ``the Revision 1 date of this 
service bulletin,'' this AD requires using ``the effective date of 
this AD.''
    (2) Where Boeing Service Bulletin 737-53-1246, Revision 1, dated 
May 30, 2018, specifies contacting Boeing for repair instructions or 
for work instructions: This AD requires doing the repair or the work 
instructions and doing applicable on-condition actions using a 
method approved in accordance with the procedures specified in 
paragraph (j) of this AD.

(j) Alternative Methods of Compliance (AMOCs)

    (1) The Manager, Seattle ACO Branch, 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 certification office, send it to the attention of the 
person identified in paragraph (k)(1) of this AD. Information may be 
emailed to: [email protected].
    (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 Branch, FAA, 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 (i) of this AD: For service 
information that contains steps that are labeled as 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 Alan Pohl, 
Aerospace Engineer, Airframe Section, FAA, Seattle ACO Branch, 2200 
South 216th St., Des Moines, WA 98198; phone and fax: 206-231-3527; 
email: [email protected].
    (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 Standards Branch, 2200 South 216th 
St., Des Moines, WA. For information on the availability of this 
material at the FAA, call 206-231-3195.

    Issued in Des Moines, Washington, on November 23, 2018.
John P. Piccola,
Acting Director, System Oversight Division, Aircraft Certification 
Service.
[FR Doc. 2018-26361 Filed 12-4-18; 8:45 am]
 BILLING CODE 4910-13-P