83_FR_23875 83 FR 23775 - Airworthiness Directives; The Boeing Company Airplanes

83 FR 23775 - Airworthiness Directives; The Boeing Company Airplanes

DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration

Federal Register Volume 83, Issue 100 (May 23, 2018)

Page Range23775-23778
FR Document2018-10920

We are adopting a new airworthiness directive (AD) for all The Boeing Company Model 737-100, -200, -200C, -300, -400, and -500 series airplanes. This AD requires repetitive high frequency eddy current (HFEC) and detailed inspections, as applicable, for cracking of certain aft vertical stiffeners; repetitive detailed inspections for cracking of time-limited repairs, as applicable; a one-time HFEC inspection for cracking of the keel beam upper chord inboard flanges; a one-time general visual inspection for cracking of a certain angle; and applicable on-condition actions. This AD was prompted by a report of cracks in the left-side and right-side keel beam upper chords and aft vertical stiffeners. We are issuing this AD to address the unsafe condition on these products.

Federal Register, Volume 83 Issue 100 (Wednesday, May 23, 2018) 
[Federal Register Volume 83, Number 100 (Wednesday, May 23, 2018)]
[Rules and Regulations]
[Pages 23775-23778]
From the Federal Register Online  [www.thefederalregister.org]
[FR Doc No: 2018-10920]



========================================================================
Rules and Regulations
                                                Federal Register
________________________________________________________________________

This section of the FEDERAL REGISTER contains regulatory documents 
having general applicability and legal effect, most of which are keyed 
to and codified in the Code of Federal Regulations, which is published 
under 50 titles pursuant to 44 U.S.C. 1510.

The Code of Federal Regulations is sold by the Superintendent of Documents. 

========================================================================


Federal Register / Vol. 83, No. 100 / Wednesday, May 23, 2018 / Rules 
and Regulations

[[Page 23775]]



DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2018-0446; Product Identifier 2018-NM-069-AD; Amendment 
39-19288; AD 2018-10-12]
RIN 2120-AA64


Airworthiness Directives; The Boeing Company Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule; request for comments.

-----------------------------------------------------------------------

SUMMARY: We are adopting a new airworthiness directive (AD) for all The 
Boeing Company Model 737-100, -200, -200C, -300, -400, and -500 series 
airplanes. This AD requires repetitive high frequency eddy current 
(HFEC) and detailed inspections, as applicable, for cracking of certain 
aft vertical stiffeners; repetitive detailed inspections for cracking 
of time-limited repairs, as applicable; a one-time HFEC inspection for 
cracking of the keel beam upper chord inboard flanges; a one-time 
general visual inspection for cracking of a certain angle; and 
applicable on-condition actions. This AD was prompted by a report of 
cracks in the left-side and right-side keel beam upper chords and aft 
vertical stiffeners. We are issuing this AD to address the unsafe 
condition on these products.

DATES: This AD is effective June 7, 2018.
    The Director of the Federal Register approved the incorporation by 
reference of a certain publication listed in this AD as of June 7, 
2018.
    We must receive comments on this AD by July 9, 2018.

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 final rule, 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-2018-0446.

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-
0446; 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 final rule, 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.

FOR FURTHER INFORMATION CONTACT: Galib Abumeri, Aerospace Engineer, 
Airframe Section, FAA, Los Angeles ACO Branch, 3960 Paramount 
Boulevard, Lakewood, CA 90712-4137; phone: 562-627-5324; fax: 562-627-
5210; email: [email protected].

SUPPLEMENTARY INFORMATION:

Discussion

    We have received a report indicating that cracks were discovered in 
the left-side and right-side keel beam upper chords and both aft 
vertical stiffeners on an airplane that had accumulated 1,304 flight 
cycles since the aft vertical stiffeners had been inspected in 
accordance with Boeing Service Bulletin 737-57A1269. The Boeing Company 
has done an analysis of the affected structure and found that the 
actual stresses on aft vertical stiffeners at left buttock line (LBL) 
and right buttock line (RBL) 6.15 are more than those used to design 
the structure. The increased stresses cause fatigue cracks in the 
stiffeners. If the aft vertical stiffeners have cracks or are severed, 
the fatigue damage may extend into the adjacent keel beam structure. 
The Boeing Company has determined that the existing inspections in 
Boeing Service Bulletin 737-57A1269, required by AD 2005-20-01, 
Amendment 39-14294 (70 FR 56358, September 27, 2005) (``AD 2005-20-
01''), do not provide sufficient inspection intervals for timely crack 
detection in the aft vertical stiffeners. Cracking of the aft vertical 
stiffeners, if not addressed, could result in the inability of the keel 
beam structure to sustain required flight loads, which could adversely 
affect the structural integrity of the airplane.
    We have determined that both AD 2005-20-01 and this AD must be done 
in order to address the identified unsafe condition. Boeing plans to 
issue a revision to Service Bulletin 737-57A1269 in the near future and 
at that time we may consider superseding AD 2005-20-01.

Related Service Information Under 1 CFR Part 51

    We reviewed Boeing Alert Requirements Bulletin 737-57A1339 RB, 
dated April 16, 2018. The service information describes procedures for 
repetitive surface HFEC and detailed inspections for cracking of the 
aft vertical stiffeners; repetitive detailed inspections for cracking 
of time-limited repairs; a one-time surface HFEC inspection for 
cracking of the keel beam upper chord inboard flanges and a general 
visual inspection for cracking of the associated angle; and applicable 
on-condition actions. 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 issuing this AD because we evaluated all the relevant 
information and determined the unsafe condition described previously is 
likely to exist or

[[Page 23776]]

develop in other products of the same type design.

AD Requirements

    This AD requires accomplishing the actions identified as ``RC'' 
(required for compliance) in the Accomplishment Instructions of Boeing 
Alert Requirements Bulletin 737-57A1339 RB, dated April 16, 2018, 
described previously, except for any differences identified as 
exceptions in the regulatory text of this 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-2018-0446.

Explanation of Requirements Bulletin

    The FAA worked in conjunction with industry, under the 
Airworthiness Directives Implementation Aviation Rulemaking Committee 
(AD ARC), to enhance the AD system. One enhancement is a process for 
annotating which steps in the service information are ``required for 
compliance'' (RC) with an AD. Boeing has implemented this RC concept 
into Boeing service bulletins. In an effort to further improve the 
quality of ADs and AD-related Boeing service information, a joint 
process improvement initiative was worked between the FAA and Boeing. 
The initiative resulted in the development of a new process in which 
the service information more clearly identifies the actions needed to 
address the unsafe condition in the ``Accomplishment Instructions.'' 
The new process results in a Boeing Requirements Bulletin, which 
contains only the actions needed to address the unsafe condition (i.e., 
only the RC actions).

Interim Action

    We consider this AD interim action. We are currently considering 
requiring the replacement of the vertical stiffeners on certain 
airplanes, which would constitute terminating action for certain 
inspections required by this AD action. The planned compliance time for 
replacing the vertical stiffeners would allow enough time to provide 
notice and opportunity for prior public comment on the merits of the 
modification.

FAA's Justification and Determination of the Effective Date

    An unsafe condition exists that requires the immediate adoption of 
this AD without providing an opportunity for public comments prior to 
adoption. The FAA has found that the risk to the flying public 
justifies waiving notice and comment prior to adoption of this rule 
because cracks in the keel beam upper chords could result in the 
inability of the keel beam structure to sustain required flight loads, 
which could adversely affect the structural integrity of the airplane. 
Therefore, we find good cause that notice and opportunity for prior 
public comment are impracticable. In addition, for the reason(s) stated 
above, we find that good cause exists for making this amendment 
effective in less than 30 days.

Comments Invited

    This AD is a final rule that involves requirements affecting flight 
safety and was not preceded by notice and an opportunity for public 
comment. However, we invite you to send any written data, views, or 
arguments about this final rule. Send your comments to an address 
listed under the ADDRESSES section. Include the docket number FAA-2018-
0446 and Product Identifier 2018-NM-069-AD at the beginning of your 
comments. We specifically invite comments on the overall regulatory, 
economic, environmental, and energy aspects of this final rule. We will 
consider all comments received by the closing date and may amend this 
final rule 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 final rule.

Costs of Compliance

    We estimate that this AD affects 67 airplanes of U.S. registry. We 
estimate the following costs to comply with this AD:

                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
                                                                                                Cost on U.S.
            Action                   Labor cost         Parts cost      Cost per product          operators
----------------------------------------------------------------------------------------------------------------
Surface HFEC and detailed      2 work-hours x $85                 $0  $170 per inspection   Up to $11,390 per
 inspections of aft vertical    per hour = $170 per                    cycle.                inspection cycle.
 stiffeners (for                inspection cycle.
 Configuration 1 airplanes).
Detailed inspection of aft     2 work-hours x $85                  0  $170 per inspection   Up to $11,390 per
 vertical stiffeners and time-  per hour = $170.                       cycle.                inspection cycle.
 limited repair (for
 Configuration 2 airplanes).
Surface HFEC inspection of     2 work-hours x $85                  0  $170................  $11,390.
 the keel beam upper chord      per hour = $170.
 inboard flanges and a
 general visual inspection of
 the angle (for all
 airplanes).
----------------------------------------------------------------------------------------------------------------

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

[[Page 23777]]

Division, but during this transition period, the Executive Director has 
delegated the authority to issue ADs applicable to transport category 
airplanes and associated appliances to the Director of the System 
Oversight Division.

Regulatory Findings

    This AD will not have federalism implications under Executive Order 
13132. This AD 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.
    For the reasons discussed above, I certify that this AD:
    (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),
    (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.

Adoption of the Amendment

    Accordingly, under the authority delegated to me by the 
Administrator, the FAA amends 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):

2018-10-12 The Boeing Company: Amendment 39-19288; Docket No. FAA-
2018-0446; Product Identifier 2018-NM-069-AD.

(a) Effective Date

    This AD is effective June 7, 2018.

(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 57, Wings; 53, 
Fuselage.

(e) Unsafe Condition

    This AD was prompted by a report of cracks in the left-side and 
right-side keel beam upper chords and aft vertical stiffeners. 
Cracks in the aft vertical stiffeners may lead to the inability of 
the keel beam structure to sustain required flight loads, which 
could adversely affect the structural integrity of the airplane.

(f) Compliance

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

(g) Required Actions for Group 1 Airplanes

    For airplanes identified as Group 1 in Boeing Alert Requirements 
Bulletin 737-57A1339 RB, dated April 16, 2018: Within 120 days after 
the effective date of this AD, inspect the airplane and do all 
applicable corrective actions using a method approved in accordance 
with the procedures specified in paragraph (k) of this AD.

(h) Required Actions for Group 2 Airplanes

    Except as required by paragraph (i) of this AD: For airplanes 
identified as Group 2 in Boeing Alert Requirements Bulletin 737-
57A1339 RB, dated April 16, 2018, at the applicable times specified 
in the ``Compliance'' paragraph of Boeing Alert Requirements 
Bulletin 737-57A1339 RB, dated April 16, 2018, do all applicable 
actions identified in, and in accordance with, the Accomplishment 
Instructions of Boeing Alert Requirements Bulletin 737-57A1339 RB, 
dated April 16, 2018.
    Note 1 to paragraph (h) of this AD: Guidance for accomplishing 
the actions required by this AD can be found in Boeing Alert Service 
Bulletin 737-57A1339, dated April 16, 2018, which is referred to in 
Boeing Alert Requirements Bulletin 737-57A1339 RB, dated April 16, 
2018.

(i) Exceptions to Service Information Specifications

    (1) For purposes of determining compliance with the requirements 
of this AD: Where Boeing Alert Requirements Bulletin 737-57A1339 RB, 
dated April 16, 2018, uses the phrase ``the original issue date of 
Requirements Bulletin 737-57A1339 RB,'' this AD requires using the 
effective date of this AD.
    (2) Where Boeing Alert Requirements Bulletin 737-57A1339 RB, 
dated April 16, 2018, specifies contacting Boeing, this AD requires 
repair using a method approved in accordance with the procedures 
specified in paragraph (k) of this AD.

(j) Optional Terminating Action for Repetitive Inspections

    Removal of the time-limited repair and accomplishment of 
additional actions in accordance with the Accomplishment 
Instructions of Boeing Alert Requirements Bulletin 737-57A1339 RB, 
dated April 16, 2018, terminate the repetitive inspections of the 
aft vertical stiffeners and time-limited repair, as specified in the 
Accomplishment Instructions of Boeing Alert Requirements Bulletin 
737-57A1339 RB, dated April 16, 2018, and required by paragraph (h) 
of this AD.

(k) Alternative Methods of Compliance (AMOCs)

    (1) The Manager, Los Angeles 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 (l)(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, Los Angeles ACO Branch, 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.

(l) Related Information

    (1) For more information about this AD, contact Galib Abumeri, 
Aerospace Engineer, Airframe Section, FAA, Los Angeles ACO Branch, 
3960 Paramount Boulevard, Lakewood, CA 90712-4137; phone: 562-627-
5324; fax: 562-627-5210; email: [email protected].
    (2) Service information identified in this AD that is not 
incorporated by reference is available at the addresses specified in 
paragraphs (m)(3) and (m)(4) of this AD.

(m) Material Incorporated by Reference

    (1) The Director of the Federal Register approved the 
incorporation by reference (IBR) of the service information listed 
in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51.
    (2) You must use this service information as applicable to do 
the actions required by this AD, unless the AD specifies otherwise.
    (i) Boeing Alert Requirements Bulletin 737-57A1339 RB, dated 
April 16, 2018.
    (ii) Reserved.
    (3) 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.
    (4) You may view this 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.
    (5) You may view this service information that is incorporated 
by reference at the National Archives and Records

[[Page 23778]]

Administration (NARA). For information on the availability of this 
material at NARA, call 202-741-6030, or go to: http://www.archives.gov/federal-register/cfr/ibr-locations.html.

    Issued in Des Moines, Washington, on May 11, 2018.
Michael Kaszycki,
Acting Director, System Oversight Division, Aircraft Certification 
Service.
[FR Doc. 2018-10920 Filed 5-22-18; 8:45 am]
 BILLING CODE 4910-13-P

23775 Rules and Regulations Federal Register Vol. 83, No. 100 Wednesday, May 23, 2018 This section of the FEDERAL REGISTER • Fax: 202–493–2251. 737–57A1269. The Boeing Company has contains regulatory documents having general • Mail: U.S. Department of done an analysis of the affected applicability and legal effect, most of which Transportation, Docket Operations, M– structure and found that the actual are keyed to and codified in the Code of 30, West Building Ground Floor, Room stresses on aft vertical stiffeners at left Federal Regulations, which is published under W12–140, 1200 New Jersey Avenue SE, buttock line (LBL) and right buttock line 50 titles pursuant to 44 U.S.C. 1510. Washington, DC 20590. (RBL) 6.15 are more than those used to The Code of Federal Regulations is sold by • Hand Delivery: Deliver to Mail design the structure. The increased the Superintendent of Documents. address above between 9 a.m. and 5 stresses cause fatigue cracks in the p.m., Monday through Friday, except stiffeners. If the aft vertical stiffeners Federal holidays. have cracks or are severed, the fatigue DEPARTMENT OF TRANSPORTATION For service information identified in damage may extend into the adjacent this final rule, contact Boeing keel beam structure. The Boeing Federal Aviation Administration Commercial Airplanes, Attention: Company has determined that the Contractual & Data Services (C&DS), existing inspections in Boeing Service 14 CFR Part 39 2600 Westminster Blvd., MC 110–SK57, Bulletin 737–57A1269, required by AD [Docket No. FAA–2018–0446; Product Seal Beach, CA 90740–5600; telephone 2005–20–01, Amendment 39–14294 (70 Identifier 2018–NM–069–AD; Amendment 562–797–1717; internet https:// FR 56358, September 27, 2005) (‘‘AD 39–19288; AD 2018–10–12] www.myboeingfleet.com. You may view 2005–20–01’’), do not provide sufficient RIN 2120–AA64 this referenced service information at inspection intervals for timely crack the FAA, Transport Standards Branch, detection in the aft vertical stiffeners. Airworthiness Directives; The Boeing 2200 South 216th St., Des Moines, WA. Cracking of the aft vertical stiffeners, if Company Airplanes For information on the availability of not addressed, could result in the this material at the FAA, call 206–231– inability of the keel beam structure to AGENCY: Federal Aviation 3195. It is also available on the internet sustain required flight loads, which Administration (FAA), DOT. at http://www.regulations.gov by could adversely affect the structural ACTION: Final rule; request for searching for and locating Docket No. integrity of the airplane. comments. FAA–2018–0446. We have determined that both AD SUMMARY: We are adopting a new Examining the AD Docket 2005–20–01 and this AD must be done airworthiness directive (AD) for all The in order to address the identified unsafe Boeing Company Model 737–100, –200, You may examine the AD docket on condition. Boeing plans to issue a –200C, –300, –400, and –500 series the internet at http:// revision to Service Bulletin 737– airplanes. This AD requires repetitive www.regulations.gov by searching for 57A1269 in the near future and at that high frequency eddy current (HFEC) and and locating Docket No. FAA–2018– time we may consider superseding AD detailed inspections, as applicable, for 0446; or in person at the Docket 2005–20–01. cracking of certain aft vertical stiffeners; Management Facility between 9 a.m. and 5 p.m., Monday through Friday, Related Service Information Under 1 repetitive detailed inspections for CFR Part 51 cracking of time-limited repairs, as except Federal holidays. The AD docket applicable; a one-time HFEC inspection contains this final rule, the regulatory We reviewed Boeing Alert for cracking of the keel beam upper evaluation, any comments received, and Requirements Bulletin 737–57A1339 chord inboard flanges; a one-time other information. The street address for RB, dated April 16, 2018. The service general visual inspection for cracking of the Docket Office (phone: 800–647– information describes procedures for a certain angle; and applicable on- 5527) is in the ADDRESSES section. repetitive surface HFEC and detailed condition actions. This AD was Comments will be available in the AD inspections for cracking of the aft prompted by a report of cracks in the docket shortly after receipt. vertical stiffeners; repetitive detailed left-side and right-side keel beam upper FOR FURTHER INFORMATION CONTACT: inspections for cracking of time-limited chords and aft vertical stiffeners. We are Galib Abumeri, Aerospace Engineer, repairs; a one-time surface HFEC issuing this AD to address the unsafe Airframe Section, FAA, Los Angeles inspection for cracking of the keel beam condition on these products. ACO Branch, 3960 Paramount upper chord inboard flanges and a DATES: This AD is effective June 7, 2018. Boulevard, Lakewood, CA 90712–4137; general visual inspection for cracking of The Director of the Federal Register phone: 562–627–5324; fax: 562–627– the associated angle; and applicable on- approved the incorporation by reference 5210; email: Galib.Abumeri@faa.gov. condition actions. This service of a certain publication listed in this AD SUPPLEMENTARY INFORMATION: information is reasonably available as of June 7, 2018. because the interested parties have We must receive comments on this Discussion access to it through their normal course AD by July 9, 2018. We have received a report indicating of business or by the means identified that cracks were discovered in the left- daltland on DSKBBV9HB2PROD with RULES ADDRESSES: You may send comments, in the ADDRESSES section. using the procedures found in 14 CFR side and right-side keel beam upper FAA’s Determination 11.43 and 11.45, by any of the following chords and both aft vertical stiffeners on methods: an airplane that had accumulated 1,304 We are issuing this AD because we • Federal eRulemaking Portal: Go to flight cycles since the aft vertical evaluated all the relevant information http://www.regulations.gov. Follow the stiffeners had been inspected in and determined the unsafe condition instructions for submitting comments. accordance with Boeing Service Bulletin described previously is likely to exist or VerDate Sep<11>2014 16:18 May 22, 2018 Jkt 244001 PO 00000 Frm 00001 Fmt 4700 Sfmt 4700 E:\FR\FM\23MYR1.SGM 23MYR1

23776 Federal Register / Vol. 83, No. 100 / Wednesday, May 23, 2018 / Rules and Regulations develop in other products of the same information more clearly identifies the opportunity for prior public comment type design. actions needed to address the unsafe are impracticable. In addition, for the condition in the ‘‘Accomplishment reason(s) stated above, we find that good AD Requirements Instructions.’’ The new process results cause exists for making this amendment This AD requires accomplishing the in a Boeing Requirements Bulletin, effective in less than 30 days. actions identified as ‘‘RC’’ (required for which contains only the actions needed compliance) in the Accomplishment Comments Invited to address the unsafe condition (i.e., Instructions of Boeing Alert only the RC actions). This AD is a final rule that involves Requirements Bulletin 737–57A1339 requirements affecting flight safety and RB, dated April 16, 2018, described Interim Action was not preceded by notice and an previously, except for any differences We consider this AD interim action. opportunity for public comment. identified as exceptions in the We are currently considering requiring However, we invite you to send any regulatory text of this AD. the replacement of the vertical stiffeners written data, views, or arguments about For information on the procedures on certain airplanes, which would this final rule. Send your comments to and compliance times, see this service constitute terminating action for certain an address listed under the ADDRESSES information at http:// inspections required by this AD action. section. Include the docket number www.regulations.gov by searching for The planned compliance time for FAA–2018–0446 and Product Identifier and locating Docket No. FAA–2018– replacing the vertical stiffeners would 2018–NM–069–AD at the beginning of 0446. allow enough time to provide notice and your comments. We specifically invite opportunity for prior public comment comments on the overall regulatory, Explanation of Requirements Bulletin on the merits of the modification. economic, environmental, and energy The FAA worked in conjunction with aspects of this final rule. We will industry, under the Airworthiness FAA’s Justification and Determination consider all comments received by the Directives Implementation Aviation of the Effective Date closing date and may amend this final Rulemaking Committee (AD ARC), to An unsafe condition exists that rule because of those comments. enhance the AD system. One requires the immediate adoption of this We will post all comments we enhancement is a process for annotating AD without providing an opportunity receive, without change, to http:// which steps in the service information for public comments prior to adoption. www.regulations.gov, including any are ‘‘required for compliance’’ (RC) with The FAA has found that the risk to the personal information you provide. We an AD. Boeing has implemented this RC flying public justifies waiving notice will also post a report summarizing each concept into Boeing service bulletins. In and comment prior to adoption of this substantive verbal contact we receive an effort to further improve the quality rule because cracks in the keel beam about this final rule. of ADs and AD-related Boeing service upper chords could result in the information, a joint process inability of the keel beam structure to Costs of Compliance improvement initiative was worked sustain required flight loads, which We estimate that this AD affects 67 between the FAA and Boeing. The could adversely affect the structural airplanes of U.S. registry. We estimate initiative resulted in the development of integrity of the airplane. Therefore, we the following costs to comply with this a new process in which the service find good cause that notice and AD: ESTIMATED COSTS Action Labor cost Parts cost Cost per product Cost on U.S. operators Surface HFEC and detailed 2 work-hours × $85 per hour $0 $170 per inspection cycle ...... Up to $11,390 per inspection inspections of aft vertical = $170 per inspection cycle. cycle. stiffeners (for Configuration 1 airplanes). Detailed inspection of aft 2 work-hours × $85 per hour 0 $170 per inspection cycle ...... Up to $11,390 per inspection vertical stiffeners and time- = $170. cycle. limited repair (for Configura- tion 2 airplanes). Surface HFEC inspection of 2 work-hours × $85 per hour 0 $170 ....................................... $11,390. the keel beam upper chord = $170. inboard flanges and a gen- eral visual inspection of the angle (for all airplanes). We have received no definitive data detail the scope of the Agency’s is within the scope of that authority that would enable us to provide cost authority. because it addresses an unsafe condition estimates for the on-condition actions We are issuing this rulemaking under that is likely to exist or develop on specified in this AD. the authority described in Subtitle VII, products identified in this rulemaking Part A, Subpart III, Section 44701: action. Authority for This Rulemaking ‘‘General requirements.’’ Under that This AD is issued in accordance with daltland on DSKBBV9HB2PROD with RULES Title 49 of the United States Code section, Congress charges the FAA with authority delegated by the Executive specifies the FAA’s authority to issue promoting safe flight of civil aircraft in Director, Aircraft Certification Service, rules on aviation safety. Subtitle I, air commerce by prescribing regulations as authorized by FAA Order 8000.51C. section 106, describes the authority of for practices, methods, and procedures In accordance with that order, issuance the FAA Administrator. ‘‘Subtitle VII: the Administrator finds necessary for of ADs is normally a function of the Aviation Programs’’ describes in more safety in air commerce. This regulation Compliance and Airworthiness VerDate Sep<11>2014 16:18 May 22, 2018 Jkt 244001 PO 00000 Frm 00002 Fmt 4700 Sfmt 4700 E:\FR\FM\23MYR1.SGM 23MYR1

Federal Register / Vol. 83, No. 100 / Wednesday, May 23, 2018 / Rules and Regulations 23777 Division, but during this transition (d) Subject Instructions of Boeing Alert Requirements period, the Executive Director has Air Transport Association (ATA) of Bulletin 737–57A1339 RB, dated April 16, delegated the authority to issue ADs America Code 57, Wings; 53, Fuselage. 2018, and required by paragraph (h) of this AD. applicable to transport category (e) Unsafe Condition airplanes and associated appliances to (k) Alternative Methods of Compliance This AD was prompted by a report of (AMOCs) the Director of the System Oversight cracks in the left-side and right-side keel Division. beam upper chords and aft vertical stiffeners. (1) The Manager, Los Angeles ACO Branch, Cracks in the aft vertical stiffeners may lead FAA, has the authority to approve AMOCs Regulatory Findings for this AD, if requested using the procedures to the inability of the keel beam structure to This AD will not have federalism sustain required flight loads, which could found in 14 CFR 39.19. In accordance with implications under Executive Order adversely affect the structural integrity of the 14 CFR 39.19, send your request to your airplane. principal inspector or local Flight Standards 13132. This AD will not have a District Office, as appropriate. If sending substantial direct effect on the States, on (f) Compliance information directly to the manager of the the relationship between the national Comply with this AD within the certification office, send it to the attention of government and the States, or on the compliance times specified, unless already the person identified in paragraph (l)(1) of distribution of power and done. this AD. Information may be emailed to: 9- responsibilities among the various ANM-LAACO-AMOC-Requests@faa.gov. levels of government. (g) Required Actions for Group 1 Airplanes (2) Before using any approved AMOC, For the reasons discussed above, I For airplanes identified as Group 1 in notify your appropriate principal inspector, certify that this AD: Boeing Alert Requirements Bulletin 737– or lacking a principal inspector, the manager (1) Is not a ‘‘significant regulatory 57A1339 RB, dated April 16, 2018: Within of the local flight standards district office/ 120 days after the effective date of this AD, certificate holding district office. action’’ under Executive Order 12866, (3) An AMOC that provides an acceptable inspect the airplane and do all applicable (2) Is not a ‘‘significant rule’’ under level of safety may be used for any repair, corrective actions using a method approved DOT Regulatory Policies and Procedures in accordance with the procedures specified modification, or alteration required by this (44 FR 11034, February 26, 1979), in paragraph (k) of this AD. AD if it is approved by the Boeing (3) Will not affect intrastate aviation Commercial Airplanes Organization in Alaska, and (h) Required Actions for Group 2 Airplanes Designation Authorization (ODA) that has (4) Will not have a significant Except as required by paragraph (i) of this been authorized by the Manager, Los Angeles economic impact, positive or negative, AD: For airplanes identified as Group 2 in ACO Branch, to make those findings. To be on a substantial number of small entities Boeing Alert Requirements Bulletin 737– approved, the repair method, modification under the criteria of the Regulatory 57A1339 RB, dated April 16, 2018, at the deviation, or alteration deviation must meet applicable times specified in the the certification basis of the airplane, and the Flexibility Act. approval must specifically refer to this AD. ‘‘Compliance’’ paragraph of Boeing Alert List of Subjects in 14 CFR Part 39 Requirements Bulletin 737–57A1339 RB, dated April 16, 2018, do all applicable (l) Related Information Air transportation, Aircraft, Aviation actions identified in, and in accordance with, (1) For more information about this AD, safety, Incorporation by reference, the Accomplishment Instructions of Boeing contact Galib Abumeri, Aerospace Engineer, Safety. Alert Requirements Bulletin 737–57A1339 Airframe Section, FAA, Los Angeles ACO RB, dated April 16, 2018. Branch, 3960 Paramount Boulevard, Adoption of the Amendment Note 1 to paragraph (h) of this AD: Lakewood, CA 90712–4137; phone: 562–627– Accordingly, under the authority Guidance for accomplishing the actions 5324; fax: 562–627–5210; email: delegated to me by the Administrator, required by this AD can be found in Boeing Galib.Abumeri@faa.gov. the FAA amends 14 CFR part 39 as Alert Service Bulletin 737–57A1339, dated (2) Service information identified in this April 16, 2018, which is referred to in Boeing AD that is not incorporated by reference is follows: available at the addresses specified in Alert Requirements Bulletin 737–57A1339 RB, dated April 16, 2018. paragraphs (m)(3) and (m)(4) of this AD. PART 39—AIRWORTHINESS DIRECTIVES (i) Exceptions to Service Information (m) Material Incorporated by Reference Specifications (1) The Director of the Federal Register ■ 1. The authority citation for part 39 (1) For purposes of determining approved the incorporation by reference continues to read as follows: compliance with the requirements of this AD: (IBR) of the service information listed in this Authority: 49 U.S.C. 106(g), 40113, 44701. Where Boeing Alert Requirements Bulletin paragraph under 5 U.S.C. 552(a) and 1 CFR 737–57A1339 RB, dated April 16, 2018, uses part 51. § 39.13 [Amended] the phrase ‘‘the original issue date of (2) You must use this service information Requirements Bulletin 737–57A1339 RB,’’ as applicable to do the actions required by ■ 2. The FAA amends § 39.13 by adding this AD, unless the AD specifies otherwise. this AD requires using the effective date of the following new airworthiness this AD. (i) Boeing Alert Requirements Bulletin directive (AD): (2) Where Boeing Alert Requirements 737–57A1339 RB, dated April 16, 2018. 2018–10–12 The Boeing Company: Bulletin 737–57A1339 RB, dated April 16, (ii) Reserved. Amendment 39–19288; Docket No. 2018, specifies contacting Boeing, this AD (3) For service information identified in FAA–2018–0446; Product Identifier requires repair using a method approved in this AD, contact Boeing Commercial 2018–NM–069–AD. accordance with the procedures specified in Airplanes, Attention: Contractual & Data paragraph (k) of this AD. Services (C&DS), 2600 Westminster Blvd., (a) Effective Date MC 110–SK57, Seal Beach, CA 90740–5600; (j) Optional Terminating Action for telephone 562–797–1717; internet https:// This AD is effective June 7, 2018. Repetitive Inspections www.myboeingfleet.com. (b) Affected ADs Removal of the time-limited repair and (4) You may view this service information daltland on DSKBBV9HB2PROD with RULES None. accomplishment of additional actions in at the FAA, Transport Standards Branch, accordance with the Accomplishment 2200 South 216th St., Des Moines, WA. For (c) Applicability Instructions of Boeing Alert Requirements information on the availability of this This AD applies to all The Boeing Bulletin 737–57A1339 RB, dated April 16, material at the FAA, call 206–231–3195. Company Model 737–100, –200, –200C, 2018, terminate the repetitive inspections of (5) You may view this service information –300, –400, and –500 series airplanes, the aft vertical stiffeners and time-limited that is incorporated by reference at the certificated in any category. repair, as specified in the Accomplishment National Archives and Records VerDate Sep<11>2014 16:18 May 22, 2018 Jkt 244001 PO 00000 Frm 00003 Fmt 4700 Sfmt 4700 E:\FR\FM\23MYR1.SGM 23MYR1

23778 Federal Register / Vol. 83, No. 100 / Wednesday, May 23, 2018 / Rules and Regulations Administration (NARA). For information on Examining the AD Docket of the helicopter frame and subsequent the availability of this material at NARA, call loss of control of the helicopter. To 202–741–6030, or go to: http:// You may examine the AD docket on the internet at http:// address this condition, EASA issued AD www.archives.gov/federal-register/cfr/ibr- No. 2014–0098–E to require repetitive locations.html. www.regulations.gov by searching for and locating Docket No. FAA–2015– inspections of the splices for a crack, as Issued in Des Moines, Washington, on May well as cutting out the rail support 11, 2018. 3883; or in person at Docket Operations between 9 a.m. and 5 p.m., Monday junction profiles to provide a Michael Kaszycki, convenient access to identify cracks in through Friday, except Federal holidays. Acting Director, System Oversight Division, The AD docket contains this AD, the a splice. Aircraft Certification Service. Since the NPRM was issued, the European Aviation Safety Agency [FR Doc. 2018–10920 Filed 5–22–18; 8:45 am] FAA’s Aircraft Certification Service has (EASA) AD, any incorporated-by- BILLING CODE 4910–13–P changed its organizational structure. reference service information, the The new structure replaces product economic evaluation, any comments directorates with functional divisions. received, and other information. The DEPARTMENT OF TRANSPORTATION We have revised some of the office titles street address for Docket Operations and nomenclature throughout this Final Federal Aviation Administration (phone: 800–647–5527) is U.S. rule to reflect the new organizational Department of Transportation, Docket changes. Additional information about 14 CFR Part 39 Operations, M–30, West Building the new structure can be found in the Ground Floor, Room W12–140, 1200 Notice published on July 25, 2017 (82 [Docket No. FAA–2015–3883; Product New Jersey Avenue SE, Washington, DC FR 34564). Identifier 2014–SW–029–AD; Amendment 20590. 39–19289; AD 2018–11–01] FOR FURTHER INFORMATION CONTACT: Gary Comments Roach, Aviation Safety Engineer, After our NPRM was published, we RIN 2120–AA64 Regulations & Policy Section, Rotorcraft received comments from a commenter Standards Branch, FAA, 10101 who raised three issues. Airworthiness Directives; Airbus Hillwood Pkwy., Fort Worth, TX 76177; Helicopters telephone (817) 222–5110; email Request AGENCY: Federal Aviation gary.b.roach@faa.gov. The commenter requested that we Administration (FAA), DOT. SUPPLEMENTARY INFORMATION: revise the applicability of the AD to ACTION: Final rule. exempt helicopters that are ‘‘post mod Discussion 07 26493 or RDAS 332–1284–13.’’ SUMMARY: We are adopting a new On January 5, 2016, at 81 FR 191, the We partially agree. Modification airworthiness directive (AD) for Airbus Federal Register published our notice of (MOD) 0726493 or repair design Helicopters Model AS332L2 and proposed rulemaking (NPRM), which approval sheet (RDAS) 332–1284–13 EC225LP helicopters. This AD requires proposed to amend 14 CFR part 39 by specify installing a stainless steel installing a cut-out for the left-hand adding an AD that would apply to doubler to reduce stress in the splice (LH) and right-hand (RH) rail support Model AS332L2 and Model EC225LP and frame, thereby eliminating the junction profiles and inspecting splices, helicopters with an extended aluminum unsafe condition. We disagree with frame 5295, and related equipment for splice installed on frame 5295. The exempting ‘‘post mod’’ helicopters, a crack. This AD was prompted by NPRM proposed to require installing a however, as the stainless steel doubler reports of cracks on frame 5295 and on cut-out for the LH and RH rail support could be removed (subjecting the splices installed to prevent those cracks. junction profiles and inspecting splices, helicopter again to the unsafe condition) The actions of this AD are intended to frame 5295, and related equipment for and the helicopter would still be in a prevent an unsafe condition on these a crack. The proposed requirements ‘‘post mod’’ configuration. Instead, we products. were intended to detect a crack in frame have changed the applicability to 5295, which could lead to structural exempt helicopters with the steel splice DATES: This AD is effective June 27, failure of the frame and loss of control kit installed that pertains to MOD 2018. of the helicopter. 0726493. The Director of the Federal Register The NPRM was prompted by AD No. The commenter requested that we approved the incorporation by reference 2014–0098–E, dated April 25, 2014, revise the compliance time of the AD to of certain documents listed in this AD issued by EASA, which is the Technical include the flow charts from the Airbus as of June 27, 2018. Agent for the Member States of the Helicopters service information. The ADDRESSES: For service information European Union, to correct an unsafe commenter states that this information identified in this final rule, contact condition for Model AS332L2 and would explain the steps involved to Airbus Helicopters, Inc., 2701 N Forum EC225LP helicopters. EASA AD No. operators to eliminate the unsafe Drive, Grand Prairie, TX 75052; 2014–0098–E applies to helicopters condition. The commenter also telephone (972) 641–0000 or (800) 232– with a frame 5295 that have been requested that we clarify the compliance 0323; fax (972) 641–3775; or at http:// reinforced by installing aluminium times as discussed in the preamble of www.airbushelicopters.com/techpub. splices on the RH and LH fuselage the NPRM, because they appear You may review the referenced service external skins. EASA advises of a report different from those in the service information at the FAA, Office of the of a crack that initiated on a splice in information and the EASA AD. Regional Counsel, Southwest Region, We disagree. The commenter is daltland on DSKBBV9HB2PROD with RULES an area hidden by the overlapping 10101 Hillwood Pkwy., Room 6N–321, junction profile of the cabin sliding door correct that the compliance times in our Fort Worth, TX 76177. It is also rail support and then spread to the AD are different, in some measure, to available on the internet at http:// frame. those in the EASA AD. But the www.regulations.gov by searching for EASA states that a crack in frame compliance times in the AD are clear as and locating Docket No. FAA–2015– 5295, if not detected and corrected, written. The requested change is 3883. could lead to loss of structural integrity unnecessary. VerDate Sep<11>2014 16:18 May 22, 2018 Jkt 244001 PO 00000 Frm 00004 Fmt 4700 Sfmt 4700 E:\FR\FM\23MYR1.SGM 23MYR1


Document Created: 2018-05-22 23:49:30
Document Modified: 2018-05-22 23:49:30
CategoryRegulatory Information
CollectionFederal Register
sudoc ClassAE 2.7:
GS 4.107:
AE 2.106:
PublisherOffice of the Federal Register, National Archives and Records Administration
SectionRules and Regulations
ActionFinal rule; request for comments.
DatesThis AD is effective June 7, 2018.
ContactGalib Abumeri, Aerospace Engineer, Airframe Section, FAA, Los Angeles ACO Branch, 3960 Paramount Boulevard, Lakewood, CA 90712-4137; phone: 562-627-5324; fax: 562-627- 5210; email: [email protected]
FR Citation83 FR 23775 
RIN Number2120-AA64
CFR AssociatedAir Transportation; Aircraft; Aviation Safety; Incorporation by Reference and Safety
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