[Federal Register Volume 81, Number 166 (Friday, August 26, 2016)]
[Rules and Regulations]
[Pages 58816-58818]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2016-20075]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2016-4221; Directorate Identifier 2015-NM-167-AD;
Amendment 39-18619; AD 2016-17-06]
RIN 2120-AA64
Airworthiness Directives; The Boeing Company Airplanes
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Final rule.
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SUMMARY: We are adopting a new airworthiness directive (AD) for all The
Boeing Company Model 767-200 and -300 series airplanes. This AD was
prompted by an evaluation by the design approval holder (DAH)
indicating that the aft pressure bulkhead web to pressure chord joint
is subject to widespread fatigue damage (WFD). This AD requires
repetitive high frequency eddy current (HFEC) inspections of the aft
pressure bulkhead web at fasteners common to the bulkhead web and
pressure chord, around the entire circumference of the pressure chord,
for any crack, and repair of cracks. We are issuing this AD to detect
and correct cracks in the aft pressure bulkhead web. Such cracking
could result in the loss of structural integrity of the airplane.
DATES: This AD is effective September 30, 2016.
The Director of the Federal Register approved the incorporation by
reference of a certain publication listed in this AD as of September
30, 2016.
ADDRESSES: 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-
4221.
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-
4221; 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: Wayne Lockett, Aerospace Engineer,
Airframe Branch, ANM-120S, FAA, Seattle Aircraft Certification Office
(ACO), 1601 Lind Avenue SW., Renton, WA 98057-3356; phone: 425-917-
6447; fax: 425-917-6590; 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 all The Boeing Company
Model 767-200 and -300 series airplanes. The NPRM published in the
Federal Register on March 8, 2016 (81 FR 12047) (``the NPRM''). The
NPRM was prompted by an evaluation by the DAH indicating that the aft
pressure bulkhead web to pressure chord joint is subject to WFD. The
NPRM proposed to require repetitive HFEC inspections of the aft
pressure bulkhead web at fasteners common to the bulkhead web and
pressure chord, around the entire circumference of the pressure chord,
for any crack, and repair of cracks. We are issuing this AD to detect
and correct cracks in the aft pressure bulkhead web. Such cracking
could result in the loss of structural integrity of the airplane.
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. Boeing and United Airlines supported the NPRM.
Effect of Winglets on Accomplishment of the Proposed Actions
Aviation Partners Boeing stated that accomplishing supplemental
type certificate (STC) ST01920SE does not affect the actions specified
in the proposed AD.
We concur with the commenter. We have redesignated paragraph (c) of
the proposed AD as paragraph (c)(1), and added new paragraph (c)(2) to
this AD to state that installation of STC ST01920SE does not affect the
ability to accomplish the actions required by this AD. Therefore, for
airplanes on which STC ST01920SE is installed, a ``change in product''
alternative method of compliance (AMOC) approval request is not
necessary to comply with the requirements of 14 CFR 39.17.
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 changes described previously and minor editorial
changes. We have determined that these minor changes:
Are consistent with the intent that was proposed in the
NPRM for correcting the unsafe condition; and
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 767-53A0268, dated April
1, 2015. The service information describes procedures for HFEC
inspections of the aft pressure bulkhead web at fasteners
[[Page 58817]]
common to the bulkhead web and pressure chord, around the entire
circumference of the pressure chord, for any crack, and repair of
cracks. 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 296 airplanes of U.S. registry.
We estimate the following costs to comply with this AD:
Estimated Costs
----------------------------------------------------------------------------------------------------------------
Cost per Cost on U.S.
Action Labor cost Parts cost product operators
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Inspection.......................... 57 work-hours x $85 per $0 $4,845 $1,434,120
hour = $4,845.
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The size of any repair area needs to be determined before material
and work-hour costs can be calculated, so we cannot 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):
2016-17-06 The Boeing Company: Amendment 39-18619; Docket No. FAA-
2016-4221; Directorate Identifier 2015-NM-167-AD.
(a) Effective Date
This AD is effective September 30, 2016.
(b) Affected ADs
None.
(c) Applicability
(1) This AD applies to all The Boeing Company Model 767-200 and
-300 series airplanes, certificated in any category.
(2) Installation of Supplemental Type Certificate (STC)
ST01920SE (http://rgl.faa.gov/Regulatory_and_Guidance_Library/
rgstc.nsf/0/59027f43b9a7486e86257b1d006591ee/$FILE/
ST01920SE_AML.pdf) does not affect the ability to accomplish the
actions required by this AD. Therefore, for airplanes on which STC
ST01920SE is installed, a ``change in product'' alternative method
of compliance (AMOC) approval request is not necessary to comply
with the requirements of 14 CFR 39.17.
(d) Subject
Air Transport Association (ATA) of America Code 53, Fuselage.
(e) Unsafe Condition
This AD was prompted by an evaluation by the design approval
holder indicating that the aft pressure bulkhead web to pressure
chord joint is subject to widespread fatigue damage. We are issuing
this AD to detect and correct cracks in the aft pressure bulkhead
web. Such cracking could result in the loss of structural integrity
of the airplane.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(g) Repetitive Inspections
Except as required by paragraph (h) of this AD, at the
applicable time specified in paragraph 1.E., ``Compliance,'' of
Boeing Alert Service Bulletin 767-53A0268, dated April 1, 2015,
perform a surface high frequency eddy current (HFEC) inspection for
cracking of the aft pressure bulkhead web at fasteners common to the
bulkhead web and pressure chord, around the entire circumference of
the pressure chord, in accordance with the Accomplishment
Instructions of Boeing Alert Service Bulletin 767-53A0268, dated
April 1, 2015. For this AD, Group 2, Configuration 2, as specified
in Boeing Alert Service Bulletin 767-53A0268, dated April 1, 2015,
includes airplanes with the aft pressure bulkhead replaced as
specified in Boeing Alert Service Bulletin 767-53A0267. Repeat the
inspection thereafter at the applicable time specified in paragraph
1.E., ``Compliance,'' of Boeing Alert Service Bulletin 767-53A0268,
dated April 1, 2015.
(h) Service Information Exception
Where Boeing Alert Service Bulletin 767-53A0268, dated April 1,
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.
(i) Crack Repair
If any crack is found during any inspection required by
paragraph (g) of this AD, before further flight, repair the crack
using a method approved in accordance with the procedures specified
in paragraph (j) of this AD. Although Boeing Alert Service Bulletin
767-53A0268, dated April 1, 2015, specifies to contact Boeing for
repair instructions, and specifies that action as ``RC'' (Required
for Compliance), this AD requires repair as specified in this
paragraph. Installation of a
[[Page 58818]]
repair terminates the inspections required by paragraph (g) of this
AD in the area covered by the repair only.
(j) Alternative Methods of Compliance (AMOCs)
(1) The Manager, Seattle Aircraft Certification Office (ACO),
FAA, has the authority to approve AMOCs for this AD, if requested
using the procedures found in 14 CFR 39.19. In accordance with 14
CFR 39.19, send your request to your principal inspector or local
Flight Standards District Office, as appropriate. If sending
information directly to the manager of the ACO, send it to the
attention of the person identified in paragraph (k) of this AD.
Information may be emailed to: [email protected].
(2) Before using any approved AMOC, notify your appropriate
principal inspector, or lacking a principal inspector, the manager
of the local flight standards district office/certificate holding
district office.
(3) An AMOC that provides an acceptable level of safety may be
used for any repair, modification, or alteration required by this AD
if it is approved by the Boeing Commercial Airplanes Organization
Designation Authorization (ODA) that has been authorized by the
Manager, Seattle ACO, to make those findings. To be approved, the
repair method, modification deviation, or alteration deviation must
meet the certification basis of the airplane and the approval must
specifically refer to this AD.
(4) Except as required by paragraph (i) of this AD: For service
information that contains steps that are labeled as RC, the
provisions of paragraphs (j)(4)(i) and (j)(4)(ii) 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.
(k) Related Information
For more information about this AD, contact Wayne Lockett,
Aerospace Engineer, Airframe Branch, ANM-120S, FAA, Seattle ACO,
1601 Lind Avenue SW., Renton, WA 98057-3356; phone: 425-917-6447;
fax: 425-917-6590; email: [email protected].
(l) 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 767-53A0268, dated April 1,
2015.
(ii) Reserved.
(3) For 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 August 16, 2016.
Dorr M. Anderson,
Acting Manager, Transport Airplane Directorate Aircraft Certification
Service.
[FR Doc. 2016-20075 Filed 8-25-16; 8:45 am]
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