Airworthiness Directives; The Boeing Company Airplanes

[Federal Register Volume 81, Number 86 (Wednesday, May 4, 2016)]
[Rules and Regulations]
[Pages 26673-26675]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2016-10160]


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

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2015-3982; Directorate Identifier 2015-NM-098-AD; 
Amendment 39-18503; AD 2016-09-05]
RIN 2120-AA64


Airworthiness Directives; The Boeing Company Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule.

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

SUMMARY: We are adopting a new airworthiness directive (AD) for certain 
The Boeing Company Model 717-200 airplanes. This AD was prompted by 
multiple reports of the vertical stabilizer leading edge showing signs 
of fastener distress. This AD requires a detailed inspection for any 
distress of the vertical stabilizer leading edge skin, and related 
investigative and corrective actions if necessary. This AD also 
requires, for certain airplanes, repetitive detailed inspections of the 
spar cap for any loose and missing fasteners, repetitive eddy current 
testing high frequency (ETHF) and radiographic testing (RT) inspections 
of the spar cap for any crack, and related investigative and corrective 
actions if necessary. We are issuing this AD to detect and correct any 
crack in the vertical stabilizer leading edge and front spar cap, which 
may result in the structure becoming unable to support limit load, and 
may lead to the loss of the vertical stabilizer.

DATES: This AD is effective June 8, 2016.
    The Director of the Federal Register approved the incorporation by 
reference of a certain publication listed in this AD as of June 8, 
2016.

ADDRESSES: For service information identified in this final rule, 
contact Boeing Commercial Airplanes, Attention: Data & Services 
Management, 3855 Lakewood Boulevard, MC D800-0019, Long Beach, CA 
90846-0001; telephone: 206-544-5000, extension 2; fax: 206-766-5683; 
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-2015-3982.

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-2015-
3982; 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 address for the Docket Office (phone: 800-647-
5527) is Docket Management Facility, U.S. Department of Transportation, 
Docket Operations, M-30, West Building Ground Floor, Room W12-140, 1200 
New Jersey Avenue SE., Washington, DC 20590.

FOR FURTHER INFORMATION CONTACT: Eric Schrieber, Aerospace Engineer, 
Airframe Branch, ANM-120L, FAA, Los Angeles Aircraft Certification 
Office (ACO), 3960 Paramount Boulevard, Lakewood, CA 90712-4137; phone: 
562-627-5348; fax: 562-627-5210; email: [email protected].

SUPPLEMENTARY INFORMATION: 

Discussion

    We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR 
part 39 by adding an AD that would apply to certain The Boeing Company 
Model 717-200 airplanes. The NPRM published in the Federal Register on 
October 6, 2015 (80 FR 60307) (``the NPRM''). The NPRM was prompted by 
multiple reports of the vertical stabilizer leading edge showing signs 
of fastener distress. The NPRM proposed to require a detailed 
inspection for any distress of the vertical stabilizer leading edge 
skin, and related investigative and corrective actions if necessary. 
The NPRM also proposed to require, for certain airplanes, repetitive 
detailed inspections of the spar cap for any loose and missing 
fasteners, repetitive ETHF and RT inspections of the spar cap for any 
crack, and related investigative and corrective actions if necessary. 
We are issuing this AD to detect and correct any crack in the vertical 
stabilizer leading edge and front spar cap, which may result in the 
structure becoming unable to support limit load, and may lead to the 
loss of the vertical stabilizer.

Comments

    We gave the public the opportunity to participate in developing 
this AD. The following presents the comments received on the NPRM and 
the FAA's response to each comment. Boeing and an anonymous commenter 
indicated their support for the NPRM.

Request To Add Credit for Previous Actions

    Boeing requested that we add a ``Credit for Previous Actions'' 
paragraph to the proposed AD that would give credit for prior 
accomplishment of the initial inspection in paragraph (g) of the NPRM. 
Boeing stated that operator structural inspection credit has been 
incorporated as a precedent in previous ADs.
    We agree with the commenter's request. Boeing MOM-MOM-14-0437-
01B(R1), dated July 3, 2014, provides the same action and level of 
safety for the initial inspection specified in this AD. We have revised 
this AD by adding new paragraph (j) of this AD to give credit for the 
initial inspection in paragraph (g) of this AD, if that inspection was 
performed before the effective date of this AD using Boeing MOM-MOM-14-
0437-01B(R1), dated July 3, 2014. We have redesignated the remaining 
paragraphs accordingly.

Conclusion

    We reviewed the relevant data, considered the comments received, 
and determined that air safety and the public interest require adopting 
this AD with the change described previously

[[Page 26674]]

and minor editorial changes. We have determined that these minor 
changes:
    <bullet> [Agr]re consistent with the intent that was proposed in 
the NPRM for correcting the unsafe condition; and
    <bullet> Do not add any additional burden upon the public than was 
already proposed in the NPRM.
    We also determined that these changes will not increase the 
economic burden on any operator or increase the scope of this AD.

Related Service Information Under 1 CFR Part 51

    We reviewed Boeing Alert Service Bulletin 717-55A0012, dated June 
12, 2015. The service information describes procedures for a detailed 
inspection for any distress of the vertical stabilizer leading edge 
skin, a detailed inspection for any loose and missing fasteners of the 
spar cap, ETHF and RT inspections of the spar cap for any crack, and 
related investigative and corrective 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.

Costs of Compliance

    We estimate that this AD affects 106 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 for distress.........  11 work-hours x $85              $0  $935 per inspection  $99,110 per
                                    per hour = $935                      cycle.               inspection cycle.
                                    per inspection
                                    cycle.
Repetitive inspections for         7 work-hours x $85                0  595 per inspection   63,070 per
 cracking and loose and missing     per hour = $595                      cycle.               inspection cycle.
 fasteners.                         per inspection
                                    cycle.
----------------------------------------------------------------------------------------------------------------

    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.

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):

2016-09-05 The Boeing Company: Amendment 39-18503; Docket No. FAA-
2015-3982; Directorate Identifier 2015-NM-098-AD.

(a) Effective Date

    This AD is effective June 8, 2016.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to The Boeing Company Model 717-200 airplanes, 
certificated in any category, as specified in Boeing Alert Service 
Bulletin 717-55A0012, dated June 12, 2015.

(d) Subject

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

(e) Unsafe Condition

    This AD was prompted by multiple reports of the vertical 
stabilizer leading edge showing signs of fastener distress. We are 
issuing this AD to detect and correct any crack in the vertical 
stabilizer leading edge and front spar cap, which may result in the 
structure becoming unable to support limit load, and may lead to the 
loss of the vertical stabilizer.

(f) Compliance

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

(g) Initial Inspection

    Except as required by paragraph (i)(1) of this AD, at the 
applicable time specified in paragraph 1.E., ``Compliance,'' of 
Boeing Alert Service Bulletin 717-55A0012, dated June 12, 2015: Do a 
detailed inspection for any distress of the vertical stabilizer 
leading edge skin and do all applicable related investigative and 
corrective actions, in accordance with the Accomplishment 
Instructions of Boeing Alert Service Bulletin 717-55A0012, dated 
June 12, 2015, except as required by paragraph (i)(2) of this AD. Do 
all applicable related investigative and corrective actions before 
further flight.

(h) Repetitive Inspections

    For all airplanes on which no cracking was found during any 
related investigative action required by paragraph (g) of this AD: 
At the applicable time specified in paragraph 1.E., ``Compliance,'' 
of Boeing Alert Service Bulletin 717-55A0012, dated June 12, 2015, 
do the actions specified in paragraphs (h)(1) and (h)(2) of this AD 
and do all applicable related investigative and corrective actions, 
in accordance with the Accomplishment Instructions of Boeing Alert 
Service Bulletin

[[Page 26675]]

717-55A0012, dated June 12, 2015, except as required by paragraph 
(i)(2) of this AD. Do all applicable related investigative and 
corrective actions before further flight. Repeat the applicable 
inspection thereafter at the intervals specified in paragraph 1.E., 
``Compliance,'' of Boeing Alert Service Bulletin 717-55A0012, dated 
June 12, 2015.
    (1) Do detailed inspections for any loose and missing fasteners 
of the vertical stabilizer leading edge as specified in ``Part 4'' 
of Boeing Alert Service Bulletin 717-55A0012, dated June 12, 2015.
    (2) Do eddy current testing high frequency (ETHF) and 
radiographic testing (RT) inspections for any crack of the vertical 
stabilizer spar cap as specified in ``Part 2'' of Boeing Alert 
Service Bulletin 717-55A0012, dated June 12, 2015; or do ETHF 
inspections for any crack of the vertical stabilizer spar cap as 
specified in ``Part 3'' of Boeing Alert Service Bulletin 717-
55A0012, dated June 12, 2015.

(i) Exceptions to the Service Information

    (1) Where Boeing Alert Service Bulletin 717-55A0012, dated June 
12, 2015 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) If any crack is found during any inspection required by this 
AD, and Boeing Alert Service Bulletin 717-55A0012, dated June 12, 
2015, 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.

(j) Credit for Previous Actions

    This paragraph provides credit for the initial inspection 
specified in paragraph (g) of this AD, if that inspection was 
performed before the effective date of this AD using Boeing MOM-MOM-
14-0437-01B(R1), dated July 3, 2014, which is not incorporated by 
reference in 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.

(l) Related Information

    For more information about this AD, contact Eric Schrieber, 
Aerospace Engineer, Airframe Branch, ANM-120L, FAA, Los Angeles ACO, 
3960 Paramount Boulevard, Lakewood, CA 90712-4137; phone: 562-627-
5348; 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 717-55A0012, dated June 12, 
2015.
    (ii) Reserved.
    (3) For Boeing service information identified in this AD, 
contact Boeing Commercial Airplanes, Attention: Data & Services 
Management, 3855 Lakewood Boulevard, MC D800-0019, Long Beach, CA 
90846-0001; telephone: 206-544-5000, extension 2; fax: 206-766-5683; 
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 April 20, 2016.
John P. Piccola, Jr.,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2016-10160 Filed 5-3-16; 8:45 am]
 BILLING CODE 4910-13-P

The complete text was extracted from the official GovInfo HTML edition for this publication. Acquired 2026-10-09T02:28:06.759049+00:00. Text extraction preserves the recorded source wording; it does not determine current requirements.

Open the captured official edition

Source SHA-256

1223ad606987eba95a5edb769ad43b4af81eabdd9919ab1d6a3594a636a9fa3b

Text SHA-256

9c4bcc8000959b8b76127cf6ff9dc8a4693775a08864a6bed5b972e4e69b0224