81_FR_13320 81 FR 13271 - Airworthiness Directives; The Boeing Company Airplanes

81 FR 13271 - Airworthiness Directives; The Boeing Company Airplanes

DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration

Federal Register Volume 81, Issue 49 (March 14, 2016)

Page Range13271-13274
FR Document2016-05515

We are adopting a new airworthiness directive (AD) for all The Boeing Company Model 737-300, -400, and -500 series airplanes. This AD requires repetitive inspections for cracking in the horizontal and vertical flanges of the rear spar upper chord of the horizontal stabilizer, and related investigative and corrective actions if necessary. This AD was prompted by a report of cracking in the center section of the horizontal stabilizer. We are issuing this AD to detect and correct cracking of the rear spar center section of the horizontal stabilizer that could lead to departure of the horizontal stabilizer from the airplane.

Federal Register, Volume 81 Issue 49 (Monday, March 14, 2016) 
[Federal Register Volume 81, Number 49 (Monday, March 14, 2016)]
[Rules and Regulations]
[Pages 13271-13274]
From the Federal Register Online  [www.thefederalregister.org]
[FR Doc No: 2016-05515]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2016-4222; Directorate Identifier 2016-NM-017-AD; 
Amendment 39-18433; AD 2016-06-02]
RIN 2120-AA64


Airworthiness Directives; The Boeing Company Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule; request for comments.

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SUMMARY: We are adopting a new airworthiness directive (AD) for all The 
Boeing Company Model 737-300, -400, and -500 series airplanes. This AD 
requires repetitive inspections for cracking in the horizontal and 
vertical flanges of the rear spar upper chord of the horizontal 
stabilizer, and related investigative and corrective actions if 
necessary. This AD was prompted by a report of cracking in the center 
section of the horizontal stabilizer. We are issuing this AD to detect 
and correct cracking of the rear spar center section of the horizontal 
stabilizer that could lead to departure of the horizontal stabilizer 
from the airplane.

DATES: This AD is effective March 29, 2016.
    The Director of the Federal Register approved the incorporation by 
reference of a certain publication listed in this AD as of March 29, 
2016.
    We must receive comments on this AD by April 28, 2016.

ADDRESSES: You may send comments, using the procedures found in 14 CFR 
11.43 and 11.45, by any of the following methods:
     Federal eRulemaking Portal: Go to http://www.regulations.gov. Follow the instructions for submitting comments.
     Fax: 202-493-2251.
     Mail: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue SE., Washington, DC 20590.
     Hand Delivery: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue SE., Washington, DC 20590, 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: Data & Services Management, 
P.O. Box 3707, MC 2H-65, Seattle, WA 98124-2207; telephone 206-544-
5000, extension 1; fax 206-766-5680; Internet https://www.myboeingfleet.com. You may view this referenced service information 
at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., 
Renton, WA. For information on the availability of this material at the 
FAA, call 425-227-1221. It is also available on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2016-
4222.

Examining the AD Docket

    You may examine the AD docket on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2016-
4222; 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 AD, the regulatory evaluation, any comments received, and 
other information. The street address for the Docket Office (phone: 
800-647-5527) is in the ADDRESSES section. Comments will be available 
in the AD docket shortly after receipt.

FOR FURTHER INFORMATION CONTACT: Payman Soltani, Aerospace Engineer, 
Airframe Branch, ANM-120L, FAA, Los Angeles Aircraft Certification 
Office (ACO), 3960 Paramount Boulevard, Lakewood, CA 90712-4137; phone: 
562-627-5313; fax: 562-627-5210; email: [email protected].

SUPPLEMENTARY INFORMATION: 

Discussion

    We have received a report of cracking in the center section of the 
horizontal stabilizer. A review of empennage loading of the Model 737-
300, -400, and -500 series airplanes identified several loading 
discrepancies that included landing rollout (LRO) buffet condition 
within the ground-air-ground (GAG) operational loads. These loading 
discrepancies impact the operating stress level on the rear spar upper 
chord of the horizontal stabilizer center section, which can lead to 
cracking. We have determined that the inspection threshold for 
detecting the cracking needs to be lower than the existing required 
compliance threshold of 66,000 total flight cycles. This horizontal 
stabilizer center section cracking, if not corrected, could result in 
departure of the horizontal stabilizer from the airplane.

Related Rulemaking

    On April 8, 2008, we issued AD 2008-09-13, Amendment 39-15494 (73 
FR 24164, May 2, 2008), for all Boeing Model 737-300, -400, and -500 
series

[[Page 13272]]

airplanes. AD 2008-09-13 requires revising the FAA-approved maintenance 
or inspection program to include inspections that will give no less 
than the required damage tolerance rating for each structural 
significant item (SSI), doing repetitive inspections to detect cracks 
of all SSIs, and repairing cracked structure.

Related Service Information Under 1 CFR Part 51

    We reviewed Boeing Alert Service Bulletin 737-55A1100, dated 
January 26, 2016. This service information describes procedures for 
inspections for cracking in the horizontal and vertical flanges of the 
rear spar upper chord of the horizontal stabilizer, an inspection to 
identify the fasteners common to the rear spar upper chord upper gusset 
of the horizontal stabilizer center section, and related investigative 
and corrective actions if necessary. This service information is 
reasonably available because the interested parties have access to it 
through their normal course of business or by the means identified in 
the ADDRESSES section.

FAA's Determination

    We are issuing 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.

AD Requirements

    This AD requires accomplishing the actions specified in the service 
information described previously, except as discussed under 
``Differences Between this AD and the Service Information.'' For 
information on the procedures and compliance times, see this service 
information at http://www.regulations.gov by searching for and locating 
Docket No. FAA-2016-4222.
    The phrase ``related investigative actions'' is used in this AD. 
Related investigative actions are follow-on actions that (1) are 
related to the primary action, and (2) further investigate the nature 
of any condition found. Related investigative actions in an AD could 
include, for example, inspections.
    The phrase ``corrective actions'' is used in this AD. Corrective 
actions are actions that correct or address any condition found. 
Corrective actions in an AD could include, for example, repairs.

Differences Between the AD and the Service Information

    Boeing Alert Service Bulletin 737-55A1100, dated January 26, 2016, 
specifies to contact the manufacturer for instructions on how to repair 
certain conditions, but this AD would require repairing those 
conditions in one of the following ways:
     In accordance with a method that we approve; or
     Using data that meet the certification basis of the 
airplane, and that have been approved by the Boeing Commercial 
Airplanes Organization Designation Authorization (ODA) whom we have 
authorized to make those findings.
    Boeing Alert Service Bulletin 737-55A1100, dated January 26, 2016, 
specifies compliance using ``horizontal stabilizer center section 
flight cycles'' or ``center section flight cycles;'' this AD requires 
compliance for those conditions or compliance times in terms of 
airplane flight cycles.

FAA's Justification and Determination of the Effective Date

    An unsafe condition exists that requires the immediate adoption of 
this AD. The FAA has found that the risk to the flying public justifies 
waiving notice and comment prior to adoption of this rule because 
cracking of the rear spar center section of the horizontal stabilizer 
could lead to departure of the horizontal stabilizer from the airplane. 
Therefore, we find that notice and opportunity for prior public comment 
are impracticable and 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 AD. Send your comments to an address listed under 
the ADDRESSES section. Include the docket number FAA-2016-4222 and 
Directorate Identifier 2016-NM-017-AD at the beginning of your 
comments. We specifically invite comments on the overall regulatory, 
economic, environmental, and energy aspects of this AD. We will 
consider all comments received by the closing date and may amend this 
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 AD.

Costs of Compliance

    We estimate that this AD affects 400 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
----------------------------------------------------------------------------------------------------------------
Inspections....................  Up to 15 work-hours x                $0   Up to $1,275 per    Up to $510,000
                                  $85 per hour = $1,275                     inspection cycle.   per inspection
                                  per inspection cycle.                                         cycle.
----------------------------------------------------------------------------------------------------------------

    We estimate the following costs to do any necessary repairs that 
would be required based on the results of the inspection. We have no 
way of determining the number of aircraft that might need these 
repairs:

                                               On-Condition Costs
----------------------------------------------------------------------------------------------------------------
                                                                                                     Cost per
                  Action                                Labor cost                 Parts cost        product
----------------------------------------------------------------------------------------------------------------
Repair....................................  8 work-hours x $85 per hour = $680           (\1\)             $680
----------------------------------------------------------------------------------------------------------------
\1\ We have received no definitive data that would enable us to provide parts cost estimates for the actions
  specified in this AD.


[[Page 13273]]

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

    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):

2016-06-02 The Boeing Company: Amendment 39-18433; Docket No. FAA-
2016-4222; Directorate Identifier 2016-NM-017-AD.

(a) Effective Date

    This AD is effective March 29, 2016.

(b) Affected ADs

    None.

(c) Applicability

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

(d) Subject

    Air Transport Association (ATA) of America Code 55, Stabilizers.

(e) Unsafe Condition

    This AD was prompted by a report of cracking in the center 
section of the horizontal stabilizer. We are issuing this AD to 
detect and correct cracking of the rear spar center section of the 
horizontal stabilizer that could lead to departure of the horizontal 
stabilizer from the airplane.

(f) Compliance

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

(g) Actions for the Rear Spar Upper Chord Horizontal Flange of the 
Horizontal Stabilizer Center Section

    At the applicable times specified in table 1 of paragraph 1.E., 
``Compliance,'' of Boeing Alert Service Bulletin 737-55A1100, dated 
January 26, 2016, except as required by paragraphs (j)(1), (j)(2), 
and (j)(3) of this AD: Do the actions required by paragraph (g)(1) 
or (g)(2) of this AD; and do all applicable related investigative 
and corrective actions; in accordance with the Accomplishment 
Instructions of Boeing Alert Service Bulletin 737-55A1100, dated 
January 26, 2016, except as required by paragraph (j)(4) of this AD. 
Do all applicable related investigative and corrective actions at 
the applicable times specified in tables 5, 6, 7, and 8 of paragraph 
1.E., ``Compliance,'' of Boeing Alert Service Bulletin 737-55A1100, 
dated January 26, 2016. For airplanes on which ``Option 1'' of 
``CONDITION 15: SURFACE HFEC INSPECTION OF THE CHORD AROUND THE 
GUSSETS--NO CRACK FOUND'' is done as specified in the Accomplishment 
Instructions of Boeing Alert Service Bulletin 737-55A1100, dated 
January 26, 2016, repeat the inspection specified in paragraph 
(g)(2) of this AD thereafter at the applicable times specified in 
table 8 of paragraph 1.E., ``Compliance,'' of Boeing Alert Service 
Bulletin 737-55A1100, dated January 26, 2016.
    (1) Do an inspection to identify the fasteners common to the 
rear spar upper chord upper gusset of the horizontal stabilizer 
center section.
    (2) Do a surface high frequency eddy current (HFEC) inspection 
of the rear spar upper chord around the two inboard gusset plates 
common to the thrust and auxiliary beams for any crack.

(h) Repetitive Inspections of the Vertical Flange of the Rear Spar 
Upper Chord on the Horizontal Stabilizer Center Section

    At the applicable times specified in table 2 of paragraph 1.E., 
``Compliance,'' of Boeing Alert Service Bulletin 737-55A1100, dated 
January 26, 2016, except as required by paragraphs (j)(1) and (j)(2) 
of this AD: Do a surface HFEC inspection of the vertical flange of 
the rear spar upper chord; and do all applicable corrective actions; 
in accordance with the Accomplishment Instructions of Boeing Alert 
Service Bulletin 737-55A1100, dated January 26, 2016, except as 
required by paragraph (j)(4) of this AD. Do all applicable 
corrective actions before further flight. Repeat the inspection of 
the vertical flange of the rear spar upper chord thereafter at the 
time specified in table 2 of paragraph 1.E., ``Compliance,'' of 
Boeing Alert Service Bulletin 737-55A1100, dated January 26, 2016.

(i) Repetitive Inspections of the Vertical Flange Stiffener Fasteners 
of the Rear Spar Upper Chord on the Horizontal Stabilizer Center 
Section

    At the applicable times specified in table 3 of paragraph 1.E., 
``Compliance,'' of Boeing Alert Service Bulletin 737-55A1100, dated 
January 26, 2016, except as required by paragraphs (j)(1) and (j)(2) 
of this AD: Do the actions required by paragraph (i)(1) or (i)(2) of 
this AD; and do all applicable related investigative and corrective 
actions; in accordance with the Accomplishment Instructions of 
Boeing Alert Service Bulletin 737-55A1100, dated January 26, 2016, 
except as required by paragraph (j)(4) of this AD. Do all applicable 
related investigative and corrective actions at the applicable times 
specified in tables 3 and 4 of paragraph 1.E., ``Compliance,'' of 
Boeing Alert Service Bulletin 737-55A1100, dated January 26, 2016. 
Repeat the inspection specified in paragraph (i)(2) of this AD 
thereafter at the applicable times specified in tables 3 and 4 of 
paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin 
737-55A1100, dated January 26, 2016.
    (1) Do an open hole HFEC inspection of the vertical flange at 
the stiffeners of the rear spar upper chord on the horizontal 
stabilizer center section for any crack.
    (2) Do a surface HFEC inspection of the vertical flange around 
the stiffeners of the rear spar upper chord on the horizontal 
stabilizer center section for any crack.

(j) Exceptions to Service Information

    (1) Where paragraph 1.E., ``Compliance,'' of Boeing Alert 
Service Bulletin 737-55A1100, dated January 26, 2016, specifies a 
compliance time ``after the original issue date of this service 
bulletin,'' this AD requires compliance within the specified 
compliance time after the effective date of this AD.
    (2) Where paragraph 1.E., ``Compliance,'' of Boeing Alert 
Service Bulletin 737-55A1100, dated January 26, 2016, refers to 
condition or compliance time in ``horizontal stabilizer center 
section flight cycles'' or ``center section flight cycles,'' this AD 
requires

[[Page 13274]]

compliance for those conditions or compliance time in terms of 
airplane flight cycles.
    (3) The Condition column of table 1 in paragraph 1.E., 
``Compliance,'' of Boeing Alert Service Bulletin 737-55A1100, dated 
January 26, 2016, refers to ``horizontal stabilizer center section 
flight cycles.'' This AD, however, applies to the airplanes with the 
specified airplane total flight cycles as of the effective date of 
this AD.
    (4) Where Boeing Alert Service Bulletin 737-55A1100, dated 
January 26, 2016; specifies to contact Boeing for appropriate 
action: Before further flight, repair using a method approved in 
accordance with the procedures specified in paragraph (k) of this 
AD.

(k) 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 (l) 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, 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 (j)(4) of this AD: For 
service information that contains steps that are labeled as Required 
for Compliance (RC), the provisions of paragraphs (k)(4)(i) and 
(k)(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. 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.

(l) Related Information

    For more information about this AD, contact Payman Soltani, 
Aerospace Engineer, Airframe Branch, ANM-120L, FAA, Los Angeles ACO, 
3960 Paramount Boulevard, Lakewood, CA 90712-4137; phone: 562-627-
5313; fax: 562-627-5210; email: [email protected].

(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 Service Bulletin 737-55A1100, dated January 26, 
2016.
    (ii) Reserved.
    (3) For Boeing service information identified in this AD, 
contact Boeing Commercial Airplanes, Attention: Data & Services 
Management, P. O. Box 3707, MC 2H-65, Seattle, WA 98124-2207; 
telephone 206-544-5000, extension 1; fax 206-766-5680; Internet 
https://www.myboeingfleet.com.
    (4) You may view this 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.
    (5) You may view this service information that is incorporated 
by reference at the National Archives and Records 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 Renton, Washington, on March 3, 2016.
Michael Kaszycki,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2016-05515 Filed 3-11-16; 8:45 am]
BILLING CODE 4910-13-P

Federal Register / Vol. 81, No. 49 / Monday, March 14, 2016 / Rules and Regulations 13271 141, 145(g), 148, 218(a) (42 U.S.C. 10137(a), DEPARTMENT OF TRANSPORTATION telephone 206–544–5000, extension 1; 10152, 10153, 10154, 10155, 10157, 10161, fax 206–766–5680; Internet https:// 10165(g), 10168, 10198(a)) 44 U.S.C. 3504 Federal Aviation Administration www.myboeingfleet.com. You may view note. this referenced service information at 14 CFR Part 39 the FAA, Transport Airplane ■ 2. In § 72.214, Certificate of Directorate, 1601 Lind Avenue SW., Compliance 1014 is revised to read as [Docket No. FAA–2016–4222; Directorate Identifier 2016–NM–017–AD; Amendment Renton, WA. For information on the follows: availability of this material at the FAA, 39–18433; AD 2016–06–02] § 72.214 List of approved spent fuel call 425–227–1221. It is also available RIN 2120–AA64 on the Internet at http:// storage casks. www.regulations.gov by searching for * * * * * Airworthiness Directives; The Boeing and locating Docket No. FAA–2016– Company Airplanes Certificate Number: 1014. 4222. Initial Certificate Effective Date: May AGENCY: Federal Aviation Examining the AD Docket 31, 2000. Administration (FAA), DOT. You may examine the AD docket on ACTION: Final rule; request for Amendment Number 1 Effective Date: the Internet at http:// July 15, 2002. comments. www.regulations.gov by searching for Amendment Number 2 Effective Date: SUMMARY: We are adopting a new and locating Docket No. FAA–2016– June 7, 2005. airworthiness directive (AD) for all The 4222; or in person at the Docket Boeing Company Model 737–300, –400, Management Facility between 9 a.m. Amendment Number 3 Effective Date: and 5 p.m., Monday through Friday, May 29, 2007. and –500 series airplanes. This AD requires repetitive inspections for except Federal holidays. The AD docket Amendment Number 4 Effective Date: cracking in the horizontal and vertical contains this AD, the regulatory January 8, 2008. flanges of the rear spar upper chord of evaluation, any comments received, and Amendment Number 5 Effective Date: the horizontal stabilizer, and related other information. The street address for investigative and corrective actions if the Docket Office (phone: 800–647– July 14, 2008. necessary. This AD was prompted by a 5527) is in the ADDRESSES section. Amendment Number 6 Effective Date: Comments will be available in the AD report of cracking in the center section August 17, 2009. docket shortly after receipt. of the horizontal stabilizer. We are Amendment Number 7 Effective Date: issuing this AD to detect and correct FOR FURTHER INFORMATION CONTACT: December 28, 2009. cracking of the rear spar center section Payman Soltani, Aerospace Engineer, Amendment Number 8 Effective Date: of the horizontal stabilizer that could Airframe Branch, ANM–120L, FAA, Los lead to departure of the horizontal Angeles Aircraft Certification Office May 2, 2012, as corrected on November stabilizer from the airplane. (ACO), 3960 Paramount Boulevard, 16, 2012 (ADAMS Accession No. Lakewood, CA 90712–4137; phone: ML12213A170). DATES: This AD is effective March 29, 562–627–5313; fax: 562–627–5210; Amendment Number 9 Effective Date: 2016. email: Payman.Soltani@faa.gov. The Director of the Federal Register March 11, 2014. SUPPLEMENTARY INFORMATION: approved the incorporation by reference Amendment Number 10 Effective of a certain publication listed in this AD Discussion Date: May 31, 2016. as of March 29, 2016. We have received a report of cracking SAR Submitted by: Holtec We must receive comments on this in the center section of the horizontal International. AD by April 28, 2016. stabilizer. A review of empennage SAR Title: Final Safety Analysis ADDRESSES: You may send comments, loading of the Model 737–300, –400, Report for the HI–STORM 100 Cask using the procedures found in 14 CFR and –500 series airplanes identified System. 11.43 and 11.45, by any of the following several loading discrepancies that methods: included landing rollout (LRO) buffet Docket Number: 72–1014. • Federal eRulemaking Portal: Go to condition within the ground-air-ground Certificate Expiration Date: May 31, http://www.regulations.gov. Follow the (GAG) operational loads. These loading 2020. instructions for submitting comments. discrepancies impact the operating • Fax: 202–493–2251. stress level on the rear spar upper chord Model Number: HI–STORM 100. • Mail: U.S. Department of of the horizontal stabilizer center * * * * * Transportation, Docket Operations, M– section, which can lead to cracking. We Dated at Rockville, Maryland, this 2nd day 30, West Building Ground Floor, Room have determined that the inspection of March, 2016. W12–140, 1200 New Jersey Avenue SE., threshold for detecting the cracking For the Nuclear Regulatory Commission. Washington, DC 20590. needs to be lower than the existing • Hand Delivery: U.S. Department of required compliance threshold of 66,000 Victor M. McCree, Transportation, Docket Operations, M– total flight cycles. This horizontal Executive Director of Operations. 30, West Building Ground Floor, Room stabilizer center section cracking, if not [FR Doc. 2016–05711 Filed 3–11–16; 8:45 am] W12–140, 1200 New Jersey Avenue SE., corrected, could result in departure of BILLING CODE 7590–01–P Washington, DC 20590, between 9 a.m. the horizontal stabilizer from the jstallworth on DSK7TPTVN1PROD with RULES and 5 p.m., Monday through Friday, airplane. except Federal holidays. For service information identified in Related Rulemaking this final rule, contact Boeing On April 8, 2008, we issued AD 2008– Commercial Airplanes, Attention: Data 09–13, Amendment 39–15494 (73 FR & Services Management, P.O. Box 3707, 24164, May 2, 2008), for all Boeing MC 2H–65, Seattle, WA 98124–2207; Model 737–300, –400, and –500 series VerDate Sep<11>2014 11:39 Mar 11, 2016 Jkt 238001 PO 00000 Frm 00009 Fmt 4700 Sfmt 4700 E:\FR\FM\14MRR1.SGM 14MRR1

13272 Federal Register / Vol. 81, No. 49 / Monday, March 14, 2016 / Rules and Regulations airplanes. AD 2008–09–13 requires and locating Docket No. FAA–2016– AD. The FAA has found that the risk to revising the FAA-approved maintenance 4222. the flying public justifies waiving notice or inspection program to include The phrase ‘‘related investigative and comment prior to adoption of this inspections that will give no less than actions’’ is used in this AD. Related rule because cracking of the rear spar the required damage tolerance rating for investigative actions are follow-on center section of the horizontal each structural significant item (SSI), actions that (1) are related to the stabilizer could lead to departure of the doing repetitive inspections to detect primary action, and (2) further horizontal stabilizer from the airplane. cracks of all SSIs, and repairing cracked investigate the nature of any condition Therefore, we find that notice and structure. found. Related investigative actions in opportunity for prior public comment an AD could include, for example, are impracticable and that good cause Related Service Information Under 1 inspections. CFR Part 51 exists for making this amendment The phrase ‘‘corrective actions’’ is effective in less than 30 days. We reviewed Boeing Alert Service used in this AD. Corrective actions are Bulletin 737–55A1100, dated January actions that correct or address any Comments Invited 26, 2016. This service information condition found. Corrective actions in describes procedures for inspections for an AD could include, for example, This AD is a final rule that involves cracking in the horizontal and vertical repairs. requirements affecting flight safety and flanges of the rear spar upper chord of was not preceded by notice and an Differences Between the AD and the opportunity for public comment. the horizontal stabilizer, an inspection Service Information to identify the fasteners common to the However, we invite you to send any Boeing Alert Service Bulletin 737– written data, views, or arguments about rear spar upper chord upper gusset of 55A1100, dated January 26, 2016, this AD. Send your comments to an the horizontal stabilizer center section, specifies to contact the manufacturer for address listed under the ADDRESSES and related investigative and corrective instructions on how to repair certain section. Include the docket number actions if necessary. This service conditions, but this AD would require FAA–2016–4222 and Directorate information is reasonably available repairing those conditions in one of the Identifier 2016–NM–017–AD at the because the interested parties have following ways: beginning of your comments. We access to it through their normal course • In accordance with a method that of business or by the means identified specifically invite comments on the we approve; or overall regulatory, economic, in the ADDRESSES section. • Using data that meet the certification basis of the airplane, and environmental, and energy aspects of FAA’s Determination this AD. We will consider all comments that have been approved by the Boeing We are issuing this AD because we Commercial Airplanes Organization received by the closing date and may evaluated all the relevant information Designation Authorization (ODA) whom amend this AD because of those and determined the unsafe condition we have authorized to make those comments. described previously is likely to exist or findings. We will post all comments we develop in other products of the same Boeing Alert Service Bulletin 737– receive, without change, to http:// type design. 55A1100, dated January 26, 2016, www.regulations.gov, including any AD Requirements specifies compliance using ‘‘horizontal personal information you provide. We stabilizer center section flight cycles’’ or will also post a report summarizing each This AD requires accomplishing the ‘‘center section flight cycles;’’ this AD substantive verbal contact we receive actions specified in the service requires compliance for those about this AD. information described previously, conditions or compliance times in terms except as discussed under ‘‘Differences of airplane flight cycles. Costs of Compliance Between this AD and the Service Information.’’ For information on the FAA’s Justification and Determination We estimate that this AD affects 400 procedures and compliance times, see of the Effective Date airplanes of U.S. registry. this service information at http:// An unsafe condition exists that We estimate the following costs to www.regulations.gov by searching for requires the immediate adoption of this comply with this AD: ESTIMATED COSTS Action Labor cost Parts cost Cost per product Cost on U.S. operators Inspections ............. Up to 15 work-hours × $85 per hour = $0 Up to $1,275 per inspection Up to $510,000 per inspection $1,275 per inspection cycle. cycle. cycle. We estimate the following costs to do required based on the results of the determining the number of aircraft that any necessary repairs that would be inspection. We have no way of might need these repairs: ON-CONDITION COSTS jstallworth on DSK7TPTVN1PROD with RULES Cost per Action Labor cost Parts cost product Repair ............................................................... 8 work-hours × $85 per hour = $680 ....................................... ( 1) $680 1 We have received no definitive data that would enable us to provide parts cost estimates for the actions specified in this AD. VerDate Sep<11>2014 11:39 Mar 11, 2016 Jkt 238001 PO 00000 Frm 00010 Fmt 4700 Sfmt 4700 E:\FR\FM\14MRR1.SGM 14MRR1

Federal Register / Vol. 81, No. 49 / Monday, March 14, 2016 / Rules and Regulations 13273 Authority for This Rulemaking § 39.13 [Amended] upper chord around the two inboard gusset ■ 2. The FAA amends § 39.13 by adding plates common to the thrust and auxiliary Title 49 of the United States Code beams for any crack. the following new airworthiness specifies the FAA’s authority to issue directive (AD): (h) Repetitive Inspections of the Vertical rules on aviation safety. Subtitle I, Flange of the Rear Spar Upper Chord on the section 106, describes the authority of 2016–06–02 The Boeing Company: Amendment 39–18433; Docket No. Horizontal Stabilizer Center Section the FAA Administrator. ‘‘Subtitle VII: FAA–2016–4222; Directorate Identifier At the applicable times specified in table Aviation Programs’’ describes in more 2016–NM–017–AD. 2 of paragraph 1.E., ‘‘Compliance,’’ of Boeing detail the scope of the Agency’s Alert Service Bulletin 737–55A1100, dated authority. (a) Effective Date January 26, 2016, except as required by We are issuing this rulemaking under This AD is effective March 29, 2016. paragraphs (j)(1) and (j)(2) of this AD: Do a the authority described in Subtitle VII, surface HFEC inspection of the vertical flange (b) Affected ADs Part A, Subpart III, Section 44701: of the rear spar upper chord; and do all None. applicable corrective actions; in accordance ‘‘General requirements.’’ Under that with the Accomplishment Instructions of section, Congress charges the FAA with (c) Applicability Boeing Alert Service Bulletin 737–55A1100, promoting safe flight of civil aircraft in This AD applies to all The Boeing dated January 26, 2016, except as required by air commerce by prescribing regulations Company Model 737–300, –400, and –500 paragraph (j)(4) of this AD. Do all applicable for practices, methods, and procedures series airplanes, certificated in any category. corrective actions before further flight. the Administrator finds necessary for (d) Subject Repeat the inspection of the vertical flange of safety in air commerce. This regulation the rear spar upper chord thereafter at the Air Transport Association (ATA) of time specified in table 2 of paragraph 1.E., is within the scope of that authority America Code 55, Stabilizers. ‘‘Compliance,’’ of Boeing Alert Service because it addresses an unsafe condition Bulletin 737–55A1100, dated January 26, (e) Unsafe Condition that is likely to exist or develop on 2016. products identified in this rulemaking This AD was prompted by a report of action. cracking in the center section of the (i) Repetitive Inspections of the Vertical horizontal stabilizer. We are issuing this AD Flange Stiffener Fasteners of the Rear Spar Regulatory Findings to detect and correct cracking of the rear spar Upper Chord on the Horizontal Stabilizer center section of the horizontal stabilizer that Center Section This AD will not have federalism could lead to departure of the horizontal implications under Executive Order At the applicable times specified in table stabilizer from the airplane. 3 of paragraph 1.E., ‘‘Compliance,’’ of Boeing 13132. This AD will not have a (f) Compliance Alert Service Bulletin 737–55A1100, dated substantial direct effect on the States, on January 26, 2016, except as required by Comply with this AD within the the relationship between the national paragraphs (j)(1) and (j)(2) of this AD: Do the compliance times specified, unless already government and the States, or on the done. actions required by paragraph (i)(1) or (i)(2) distribution of power and of this AD; and do all applicable related responsibilities among the various (g) Actions for the Rear Spar Upper Chord investigative and corrective actions; in levels of government. Horizontal Flange of the Horizontal accordance with the Accomplishment Stabilizer Center Section Instructions of Boeing Alert Service Bulletin For the reasons discussed above, I 737–55A1100, dated January 26, 2016, except certify that this AD: At the applicable times specified in table 1 of paragraph 1.E., ‘‘Compliance,’’ of Boeing as required by paragraph (j)(4) of this AD. Do (1) Is not a ‘‘significant regulatory Alert Service Bulletin 737–55A1100, dated all applicable related investigative and action’’ under Executive Order 12866, January 26, 2016, except as required by corrective actions at the applicable times (2) Is not a ‘‘significant rule’’ under paragraphs (j)(1), (j)(2), and (j)(3) of this AD: specified in tables 3 and 4 of paragraph 1.E., DOT Regulatory Policies and Procedures Do the actions required by paragraph (g)(1) or ‘‘Compliance,’’ of Boeing Alert Service (g)(2) of this AD; and do all applicable related Bulletin 737–55A1100, dated January 26, (44 FR 11034, February 26, 1979), 2016. Repeat the inspection specified in investigative and corrective actions; in (3) Will not affect intrastate aviation accordance with the Accomplishment paragraph (i)(2) of this AD thereafter at the in Alaska, and Instructions of Boeing Alert Service Bulletin applicable times specified in tables 3 and 4 (4) Will not have a significant 737–55A1100, dated January 26, 2016, except of paragraph 1.E., ‘‘Compliance,’’ of Boeing economic impact, positive or negative, as required by paragraph (j)(4) of this AD. Do Alert Service Bulletin 737–55A1100, dated on a substantial number of small entities all applicable related investigative and January 26, 2016. corrective actions at the applicable times (1) Do an open hole HFEC inspection of the under the criteria of the Regulatory vertical flange at the stiffeners of the rear spar specified in tables 5, 6, 7, and 8 of paragraph Flexibility Act. 1.E., ‘‘Compliance,’’ of Boeing Alert Service upper chord on the horizontal stabilizer List of Subjects in 14 CFR Part 39 Bulletin 737–55A1100, dated January 26, center section for any crack. 2016. For airplanes on which ‘‘Option 1’’ of (2) Do a surface HFEC inspection of the Air transportation, Aircraft, Aviation ‘‘CONDITION 15: SURFACE HFEC vertical flange around the stiffeners of the safety, Incorporation by reference, INSPECTION OF THE CHORD AROUND rear spar upper chord on the horizontal Safety. THE GUSSETS—NO CRACK FOUND’’ is stabilizer center section for any crack. done as specified in the Accomplishment Adoption of the Amendment Instructions of Boeing Alert Service Bulletin (j) Exceptions to Service Information 737–55A1100, dated January 26, 2016, repeat (1) Where paragraph 1.E., ‘‘Compliance,’’ of Accordingly, under the authority the inspection specified in paragraph (g)(2) of Boeing Alert Service Bulletin 737–55A1100, delegated to me by the Administrator, this AD thereafter at the applicable times dated January 26, 2016, specifies a the FAA amends 14 CFR part 39 as specified in table 8 of paragraph 1.E., compliance time ‘‘after the original issue date follows: ‘‘Compliance,’’ of Boeing Alert Service of this service bulletin,’’ this AD requires jstallworth on DSK7TPTVN1PROD with RULES Bulletin 737–55A1100, dated January 26, compliance within the specified compliance PART 39—AIRWORTHINESS 2016. time after the effective date of this AD. DIRECTIVES (1) Do an inspection to identify the (2) Where paragraph 1.E., ‘‘Compliance,’’ of fasteners common to the rear spar upper Boeing Alert Service Bulletin 737–55A1100, ■ 1. The authority citation for part 39 chord upper gusset of the horizontal dated January 26, 2016, refers to condition or stabilizer center section. compliance time in ‘‘horizontal stabilizer continues to read as follows: (2) Do a surface high frequency eddy center section flight cycles’’ or ‘‘center Authority: 49 U.S.C. 106(g), 40113, 44701. current (HFEC) inspection of the rear spar section flight cycles,’’ this AD requires VerDate Sep<11>2014 11:39 Mar 11, 2016 Jkt 238001 PO 00000 Frm 00011 Fmt 4700 Sfmt 4700 E:\FR\FM\14MRR1.SGM 14MRR1

13274 Federal Register / Vol. 81, No. 49 / Monday, March 14, 2016 / Rules and Regulations compliance for those conditions or Angeles ACO, 3960 Paramount Boulevard, DATES: This deviation is effective from compliance time in terms of airplane flight Lakewood, CA 90712–4137; phone: 562–627– 5 a.m. to 10:30 a.m. on April 17, 2016. cycles. 5313; fax: 562–627–5210; email: (3) The Condition column of table 1 in Payman.Soltani@faa.gov. ADDRESSES: The docket for this paragraph 1.E., ‘‘Compliance,’’ of Boeing deviation, [USCG–2016–0182] is (m) Material Incorporated by Reference Alert Service Bulletin 737–55A1100, dated available at http://www.regulations.gov. January 26, 2016, refers to ‘‘horizontal (1) The Director of the Federal Register approved the incorporation by reference Type the docket number in the stabilizer center section flight cycles.’’ This AD, however, applies to the airplanes with (IBR) of the service information listed in this ‘‘SEARCH’’ box and click ‘‘SEARCH.’’ the specified airplane total flight cycles as of paragraph under 5 U.S.C. 552(a) and 1 CFR Click on Open Docket Folder on the line the effective date of this AD. part 51. associated with this deviation. (4) Where Boeing Alert Service Bulletin (2) You must use this service information 737–55A1100, dated January 26, 2016; as applicable to do the actions required by FOR FURTHER INFORMATION CONTACT: If specifies to contact Boeing for appropriate this AD, unless the AD specifies otherwise. you have questions on this temporary action: Before further flight, repair using a (i) Boeing Alert Service Bulletin 737– deviation, call or email Mr. Steven 55A1100, dated January 26, 2016. method approved in accordance with the Fischer, Bridge Administrator, procedures specified in paragraph (k) of this (ii) Reserved. (3) For Boeing service information Thirteenth Coast Guard District; AD. telephone 206–220–7282, email identified in this AD, contact Boeing (k) Alternative Methods of Compliance Commercial Airplanes, Attention: Data & Steven.M.Fischer@uscg.mil. (AMOCs) Services Management, P. O. Box 3707, MC 2H–65, Seattle, WA 98124–2207; telephone SUPPLEMENTARY INFORMATION: (1) The Manager, Los Angeles Aircraft 206–544–5000, extension 1; fax 206–766– Multnomah County requested for the Certification Office (ACO), FAA, has the 5680; Internet https:// Broadway Bridge to remain closed to authority to approve AMOCs for this AD, if www.myboeingfleet.com. requested using the procedures found in 14 (4) You may view this service information vessel traffic to facilitate the safe, CFR 39.19. In accordance with 14 CFR 39.19, uninterrupted roadway passage of at the FAA, Transport Airplane Directorate, send your request to your principal inspector 1601 Lind Avenue SW., Renton, WA. For participants in the Portland Race for the or local Flight Standards District Office, as information on the availability of this Roses event. The Broadway Bridge appropriate. If sending information directly material at the FAA, call 425–227–1221. to the manager of the ACO, send it to the crosses the Willamette River at mile (5) You may view this service information 11.7, and provides 90 feet of vertical attention of the person identified in that is incorporated by reference at the paragraph (l) of this AD. Information may be National Archives and Records clearance above Columbia River Datum emailed to 9-ANM-LAACO-AMOC-Requests@ Administration (NARA). For information on 0.0 while in the closed-to-navigation faa.gov. the availability of this material at NARA, call position. This bridge operates in (2) Before using any approved AMOC, 202–741–6030, or go to: http:// accordance with 33 CFR 117.897. This notify your appropriate principal inspector, www.archives.gov/federal-register/cfr/ibr- or lacking a principal inspector, the manager deviation allows the bascule span of the locations.html. of the local flight standards district office/ Broadway Bridge across the Willamette certificate holding district office. Issued in Renton, Washington, on March 3, River, mile 11.7, to remain in the (3) An AMOC that provides an acceptable 2016. closed-to-navigation position, and need level of safety may be used for any repair, Michael Kaszycki, not open for maritime traffic from 5:00 modification, or alteration required by this Acting Manager, Transport Airplane a.m. to 10:30 a.m. on April 17, 2016. AD if it is approved by the Boeing Directorate, Aircraft Certification Service. The bridge shall operate in accordance Commercial Airplanes Organization [FR Doc. 2016–05515 Filed 3–11–16; 8:45 am] Designation Authorization (ODA) that has to 33 CFR 117.897 at all other times. BILLING CODE 4910–13–P Waterway usage on this part of the been authorized by the Manager, Los Angeles ACO, to make those findings. To be Willamette River includes vessels approved, the repair method, modification ranging from commercial tug and barge deviation, or alteration deviation must meet DEPARTMENT OF HOMELAND to small pleasure craft. We have the certification basis of the airplane, and the SECURITY coordinated with the majority of approval must specifically refer to this AD. (4) Except as required by paragraph (j)(4) Coast Guard waterway users and there were no of this AD: For service information that objections to this schedule. contains steps that are labeled as Required 33 CFR Part 117 Vessels able to pass through the for Compliance (RC), the provisions of bridge in the closed positions may do so paragraphs (k)(4)(i) and (k)(4)(ii) of this AD [Docket No. USCG–2016–0182] apply. at anytime. The bridge will be able to (i) The steps labeled as RC, including Drawbridge Operation Regulation; open for emergencies and there is no substeps under an RC step and any figures Willamette River, Portland, OR immediate alternate route for vessels to identified in an RC step, must be done to pass. The Coast Guard will also inform comply with the AD. An AMOC is required AGENCY: Coast Guard, DHS. the users of the waterways through our for any deviations to RC steps, including ACTION:Notice of deviation from Local and Broadcast Notices to Mariners substeps and identified figures. drawbridge regulation. of the change in operating schedule for (ii) Steps not labeled as RC may be deviated from using accepted methods in SUMMARY: The Coast Guard has issued a the bridge so that vessels can arrange accordance with the operator’s maintenance temporary deviation from the operating their transits to minimize any impact or inspection program without obtaining schedule that governs the Broadway caused by the temporary deviation. approval of an AMOC, provided the RC steps, Bridge across the Willamette River, mile In accordance with 33 CFR 117.35(e), jstallworth on DSK7TPTVN1PROD with RULES including substeps and identified figures, can 11.7, at Portland, OR. The deviation is still be done as specified, and the airplane the drawbridge must return to its regular necessary to accommodate the Portland operating schedule immediately at the can be put back in an airworthy condition. Race for the Roses event. This deviation end of the effective period of this (l) Related Information allows the bridge to remain in the temporary deviation. This deviation For more information about this AD, closed-to-navigation position to from the operating regulations is contact Payman Soltani, Aerospace Engineer, facilitate the safe movement of event authorized under 33 CFR 117.35. Airframe Branch, ANM–120L, FAA, Los participants across the bridge. VerDate Sep<11>2014 11:39 Mar 11, 2016 Jkt 238001 PO 00000 Frm 00012 Fmt 4700 Sfmt 4700 E:\FR\FM\14MRR1.SGM 14MRR1


Document Created: 2016-03-12 01:00:01
Document Modified: 2016-03-12 01:00:01
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 March 29, 2016.
ContactPayman Soltani, Aerospace Engineer, Airframe Branch, ANM-120L, FAA, Los Angeles Aircraft Certification Office (ACO), 3960 Paramount Boulevard, Lakewood, CA 90712-4137; phone: 562-627-5313; fax: 562-627-5210; email: [email protected]
FR Citation81 FR 13271 
RIN Number2120-AA64
CFR AssociatedAir Transportation; Aircraft; Aviation Safety; Incorporation by Reference and Safety
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