
[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]


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

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.

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

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: wayne.lockett@faa.gov.

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
----------------------------------------------------------------------------------------------------------------
Inspection..........................  57 work-hours x $85 per              $0           $4,845       $1,434,120
                                       hour = $4,845.
----------------------------------------------------------------------------------------------------------------

    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: 9-ANM-Seattle-ACO-AMOC-Requests@faa.gov.
    (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: wayne.lockett@faa.gov.

(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]
 BILLING CODE 4910-13-P


