[Federal Register Volume 81, Number 169 (Wednesday, August 31, 2016)]
[Rules and Regulations]
[Pages 59830-59834]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2016-20686]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2015-8133; Directorate Identifier 2015-NM-101-AD;
Amendment 39-18631; AD 2016-18-01]
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 737-600, -700, -700C, -800, -900, and -900ER
series airplanes. This AD was prompted by reports of heavy corrosion
and chrome damage on the forward and aft trunnion pin assemblies of the
right and left main landing gears (MLGs). This AD requires repetitive
lubrication of the forward and aft trunnion pin assemblies of the right
and left MLGs; repetitive inspections of these assemblies for corrosion
and chrome damage, and related investigative and corrective actions if
necessary; and installation of new or modified trunnion pin assembly
components, which will terminate the repetitive lubrication and
repetitive inspections. We are issuing this AD to detect and correct
heavy corrosion and chrome damage on the forward and aft trunnion pin
assemblies of the right and left MLGs, which could result in cracking
of these assemblies and collapse of the MLGs.
DATES: This AD is effective October 5, 2016.
The Director of the Federal Register approved the incorporation by
reference of a certain publication listed in this AD as of October 5,
2016.
[[Page 59831]]
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-2015-
8133.
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-
8133; 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: Alan Pohl, Aerospace Engineer,
Airframe Branch, ANM-120S, FAA Seattle Aircraft Certification Office,
1601 Lind Avenue SW., Renton, WA 98057-3356; phone: 425-917-6450; 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 certain The Boeing Company
Model 737-600, -700, -700C, -800, -900, and -900ER series airplanes.
The NPRM published in the Federal Register on December 31, 2015 (80 FR
81795) (``the NPRM''). The NPRM was prompted by reports of heavy
corrosion and chrome damage on the forward and aft trunnion pin
assemblies of the right and left MLGs. The NPRM proposed to require
repetitive lubrication of the forward and aft trunnion pin assemblies
of the right and left MLGs; repetitive inspections of these assemblies
for corrosion and chrome damage, and related investigative and
corrective actions if necessary; and installation of new or modified
trunnion pin assembly components, which would terminate the repetitive
lubrication and repetitive inspections. We are issuing this AD to
detect and correct heavy corrosion and chrome damage on the forward and
aft trunnion pin assemblies of the right and left MLGs, which could
result in cracking of these assemblies and collapse of the MLGs.
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.
Support for the NPRM
Boeing stated that it concurs with the contents of the NPRM.
Effect of Winglets on Accomplishment of the Proposed Actions
Aviation Partners Boeing stated that accomplishing Supplemental
Type Certificate (STC) ST00830SE does not affect the accomplishment of
the actions specified in the NPRM.
We concur with the commenter. We have redesignated paragraph (c) of
the proposed AD as paragraph (c)(1) and added new paragraph (c)(2) in
this AD to state that installation of STC ST00830SE does not affect the
ability to accomplish the actions required by this final rule.
Therefore, for airplanes on which STC ST00830SE 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.
Request for Clarification of Requirements
Delta Airlines (DAL) requested an explanation of how the
requirements are different between AD 2014-08-11, Amendment 39-17835
(79 FR 23903, April 29, 2014) (``AD 2014-08-11'') and the NPRM. DAL
noted that the requirements of AD 2014-08-11 include an inspection for
discrepancies of the transition radius of the MLG forward trunnion
pins, and corrective actions if necessary. DAL elaborated that this
inspection is for finish damage (scrapes through primer), signs of
corrosion, pitting, and scratches in the base metal of that area. DAL
pointed out that the NPRM requires a general visual inspection of the
MLG forward trunnion pin assembly for signs of corrosion or chrome
plating damage, and if either condition is found, a detailed inspection
of the forward trunnion pin assembly is required. DAL mentioned that
the detailed inspection requires verification that a new seal and
retainer configuration is installed, and if the overhaul limits exceed
what is specified in the component maintenance manual, replacement of
the forward trunnion pin assembly is necessary. DAL reasoned that the
forward trunnion pin inspections required by AD 2014-08-11 should be
superseded by the proposed forward trunnion pin inspections in the
NPRM. DAL stated that the detailed inspection proposed in the NPRM has
additional corrective actions if any loose or missing chrome plating is
found, beyond what is required in AD 2014-08-11. DAL also conveyed that
the inspections for signs of corrosion are the same in the NPRM and AD
2014-08-11.
We agree to provide clarification regarding how the requirements
are different between the requirements in the proposed AD and the
requirements mandated by AD 2014-08-11. The applicability of the
proposed AD includes certain The Boeing Company Model 737-600, -700, -
700C, -800, -900, and -900ER series airplanes, line numbers 1 through
3526 inclusive. The applicability of AD 2014-08-11 includes certain The
Boeing Company Model 737-600, -700, -700C, -800, -900, and -900ER
series airplanes, line numbers 1423 through 3526 inclusive. Although
certain airplane line numbers are included in the applicability of both
the proposed AD and AD 2014-08-11, the issues addressed by the NPRM and
AD 2014-08-11 are not the same. Furthermore, the inspection
instructions in the service information required for accomplishing the
actions in the proposed AD are different from the inspection
instructions in the service information required by AD 2014-08-11. The
inspections in the proposed AD focus on chrome damage and corrosion on
the shank of the forward trunnion pins, and the inspections required by
AD 2014-08-11 focus on finish scratches and corrosion in the transition
radius of the forward trunnion pins. We have not changed this AD
regarding this issue.
In addition, we note that the service information required to do
the actions required by AD 2014-08-11 (which cites Boeing Special
Attention Service Bulletin 737-32-1402, Revision 1, dated February 7,
2013), includes a recommendation by Boeing that operators accomplish
the specified actions concurrently with the actions specified in Boeing
Special Attention Service Bulletin 737-32-1448 (Boeing Special
Attention Service Bulletin 737-32-1448, Revision 1, dated May 29, 2015,
is the appropriate source of service information for accomplishing the
actions required by this AD).
[[Page 59832]]
Likewise, Boeing Special Attention Service Bulletin 737-32-1448,
Revision 1, dated May 29, 2015, includes a recommendation by Boeing
that operators accomplish the specified actions concurrently with the
actions specified in Boeing Special Attention Service Bulletin 737-32-
1402.
Request for Clarification of Lube Fittings Location
DAL requested clarification regarding the location of the lube
fittings for the forward and aft MLG trunnion pin assemblies in
paragraph (g) of the NPRM. DAL commented that the NPRM stated to do the
repetitive lubrication in accordance with Work Package 1 of the
Accomplishment Instructions of Boeing Special Attention Service
Bulletin 737-32-1448, Revision 1, dated May 29, 2015. DAL noted that
Work Package 1 of the Accomplishment Instructions of Boeing Special
Attention Service Bulletin 737-32-1448, Revision 1, dated May 29, 2015,
refers to section 12-21-11 of the Boeing 737-600/700/800/900 Aircraft
Maintenance Manual (AMM) as an accepted procedure for the repetitive
lubrication of the MLG trunnion pin assemblies. DAL stated that section
12-21-11 of the AMM specifically identifies the locations of the
trunnion bearing housing and the aft trunnion bearing, but does not
specifically identify the locations of the two lube fittings for the
forward and aft trunnion pins.
We agree with the commenter that the two lube fittings for the
forward and aft trunnion pins are not specifically mentioned in section
12-21-11 of the Boeing 737-600/700/800/900 AMM. These locations are
identified as Item [6], ``Outer Cylinder,'' on page 307 of the AMM.
However, there are only three lube fittings associated with Item [6],
so it is possible to determine which two fittings are to be used for
lubricating the forward and aft trunnion pins. We consulted with Boeing
and confirmed that the two lube fittings are located on the bottom of
the outer cylinder trunnion, directly under the pins. We have not
changed this AD regarding this issue.
Request for Clarification of Corrective Actions in Paragraph (h) of the
Proposed AD
DAL requested clarification of certain corrective actions in
paragraph (h) of the proposed AD. DAL asked if an operator can replace
an affected trunnion pin assembly instead of overhauling it. DAL
pointed out that neither the NPRM nor Boeing Special Attention Service
Bulletin 737-32-1448, Revision 1, dated May 29, 2015, specify the part
number of the replacement trunnion pin assembly. DAL asked if an
operator can replace an affected pin assembly with any properly
approved pin assembly using the Boeing 737 Aircraft Illustrated Parts
Catalog, Boeing Drawing 161A0002, ``Boeing Model 737-NG Main Landing
Gear Component Interchangeability List,'' or a similar document.
We agree with the commenter's request for clarification. Operators
may elect to replace a trunnion pin assembly with a serviceable unit in
lieu of performing an overhaul. However, operators should be aware that
some of the existing trunnion pin assemblies require modification.
Figures 9, 11, and 12 of Boeing Special Attention Service Bulletin 737-
32-1448, Revision 1, dated May 29, 2015, provide instructions for
modifying certain pin assemblies. Note (c) in each of these figures
refers to paragraph 2.C.3., ``Parts Modified and Reidentified,'' of
Boeing Special Attention Service Bulletin 737-32-1448, Revision 1,
dated May 29, 2015, which shows the existing and modified part numbers.
For use of other part numbers, such as those identified in the Boeing
737 Aircraft Illustrated Parts Catalog or Boeing Drawing 161A0002,
``Boeing Model 737-NG Main Landing Gear Component Interchangeability
List,'' operators may request an alternative method of compliance in
accordance with the procedures specified in paragraph (m) of this AD.
We have not changed this AD regarding this issue.
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 Special Attention Service Bulletin 737-32-1448,
Revision 1, dated May 29, 2015. The service information describes
procedures for lubricating the forward and aft trunnion pin assemblies
on the left and right MLGs, inspecting the forward and aft trunnion pin
assemblies for corrosion or damage, and performing corrective actions.
In addition, the service information describes procedures for
installing a new forward trunnion pin housing assembly, seal, and
retainer configuration. 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 1,023 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
----------------------------------------------------------------------------------------------------------------
Lubrication....................... 2 work-hours x $85 $0 $170 $173,910, per
per hour = $170, per lubrication cycle
lubrication cycle. (1,023 airplanes).
Inspection (Groups 1 and 2, 51 work-hours x $85 0 4,335 4,282,980, per
Configuration 1 airplanes). per hour = $4,335, inspection cycle
per inspection cycle. (988 airplanes).
Inspection (Group 3 airplanes).... 93 work-hours x $85 0 7,905 276,675, per
per hour = $7,905, inspection cycle (35
per inspection cycle. airplanes).
Replacement/overhaul (Groups 1 and 84 work-hours x $85 0 7,140 7,054,320 (988
2 airplanes). per hour = $7,140. airplanes).
Replacement/overhaul (Group 3 86 work-hours x $85 0 7,310 255,850 (35
airplanes). per hour = $7,310. airplanes).
----------------------------------------------------------------------------------------------------------------
[[Page 59833]]
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):
2016-18-01 The Boeing Company: Amendment 39-18631; Docket No. FAA-
2015-8133; Directorate Identifier 2015-NM-101-AD.
(a) Effective Date
This AD is effective October 5, 2016.
(b) Affected ADs
None.
(c) Applicability
(1) This AD applies to certain The Boeing Company Model 737-600,
-700, -700C, -800, -900, and -900ER series airplanes, certificated
in any category, as identified in Boeing Special Attention Service
Bulletin 737-32-1448, Revision 1, dated May 29, 2015.
(2) Installation of Supplemental Type Certificate (STC)
ST00830SE (http://rgl.faa.gov/Regulatory_and_Guidance_Library/rgstc.nsf/0/184DE9A71EC3FA5586257EAE00707DA6?OpenDocument&Highlight=st00830se)
does not affect the ability to accomplish the actions required by
this AD. Therefore, for airplanes on which STC ST00830SE 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 32, Landing
Gear.
(e) Unsafe Condition
This AD was prompted by reports of heavy corrosion and chrome
damage of the forward and aft trunnion pin assemblies of the right
and left main landing gears (MLGs). We are issuing this AD to detect
and correct heavy corrosion and chrome damage of the forward and aft
trunnion pin assemblies of the right and left MLGs, which could
result in cracking of these assemblies and collapse of the MLGs.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(g) Repetitive Lubrication of MLG Trunnion Pin Assemblies
For airplanes in Groups 1 and 2, Configuration 1, and airplanes
in Group 3, as identified in Boeing Special Attention Service
Bulletin 737-32-1448, Revision 1, dated May 29, 2015: Except as
required by paragraph (k) of this AD, at the applicable time
specified in Table 1 or Table 2 of paragraph 1.E., ``Compliance,''
of Boeing Special Attention Service Bulletin 737-32-1448, Revision
1, dated May 29, 2015, lubricate the forward and aft trunnion pin
assemblies of the left and right MLGs, in accordance with Work
Package 1 of the Accomplishment Instructions of Boeing Special
Attention Service Bulletin 737-32-1448, Revision 1, dated May 29,
2015. Repeat the lubrication thereafter at intervals not to exceed
those specified in paragraph 1.E., ``Compliance,'' of Boeing Special
Attention Service Bulletin 737-32-1448, Revision 1, dated May 29,
2015. Accomplishment of the actions specified in paragraph (i) of
this AD terminates the repetitive lubrication required by this
paragraph.
(h) Repetitive Inspections, Corrective Actions, and Lubrication
For airplanes in Groups 1 and 2, Configuration 1, and airplanes
in Group 3, as identified in Boeing Special Attention Service
Bulletin 737-32-1448, Revision 1, dated May 29, 2015: Except as
required by paragraph (k) of this AD, at the applicable time
specified in Table 1 or Table 2 of paragraph 1.E., ``Compliance,''
of Boeing Special Attention Service Bulletin 737-32-1448, Revision
1, dated May 29, 2015, do a general visual inspection of the left
and right MLGs at the forward and aft trunnion pin locations and the
visible surfaces of the forward and aft trunnion pin assemblies for
signs of corrosion or chrome plating damage and lubricate the
forward and aft trunnion pin assemblies, in accordance with Work
Package 2 of the Accomplishment Instructions of Boeing Special
Attention Service Bulletin 737-32-1448, Revision 1, dated May 29,
2015. Repeat the general visual inspection thereafter at intervals
not to exceed those specified in paragraph 1.E., ``Compliance,'' of
Boeing Special Attention Service Bulletin 737-32-1448, Revision 1,
dated May 29, 2015. If any discrepancy is found during any
inspection required by this paragraph, before further flight, do all
applicable related investigative and corrective actions in
accordance with Work Package 2 of the Accomplishment Instructions of
Boeing Special Attention Service Bulletin 737 32-1448, Revision 1,
dated May 29, 2015. Accomplishment of the actions required by
paragraph (i) of this AD terminates the repetitive inspections
required by this paragraph.
(i) Modification of MLG Trunnion Pin Assemblies
For airplanes in Groups 1 and 2, Configuration 1, and airplanes
in Group 3, as identified in Boeing Special Attention Service
Bulletin 737-32-1448, Revision 1, dated May 29, 2015: Except as
required by paragraph (k) of this AD, at the applicable time
specified in Table 1 or Table 2 of paragraph 1.E., ``Compliance,''
of Boeing Special Attention Service Bulletin 737-32-1448, Revision
1, dated May 29, 2015, modify and lubricate the left and right MLG
trunnion pin assemblies, and do all applicable related investigative
and corrective actions, in accordance with Work Package 3 of the
Accomplishment Instructions of Boeing Special Attention Service
Bulletin 737-32-1448, Revision 1, dated May 29, 2015.
[[Page 59834]]
Accomplishment of the actions in Work Package 3 of the
Accomplishment Instructions of Boeing Special Attention Service
Bulletin 737-32-1448, Revision 1, dated May 29, 2015, terminates the
repetitive lubrication required by paragraph (g) of this AD and the
repetitive inspections required by paragraph (h) of this AD.
(j) Replacement of MLG Forward Trunnion Pin Housing Assembly, Seal, and
Retainer
For airplanes in Groups 1 and 2, Configuration 2, as identified
in Boeing Special Attention Service Bulletin 737-32-1448, Revision
1, dated May 29, 2015: At the applicable time specified in Table 3
of paragraph 1.E., ``Compliance,'' of Boeing Special Attention
Service Bulletin 737-32-1448, Revision 1, dated May 29, 2015,
replace the seal, retainer, and support ring assembly with a new
seal and retainer configuration; install the forward trunnion pin
assembly into the housing assembly; and lubricate the forward and
aft trunnion pin assemblies for the left and right MLGs; in
accordance with Work Package 4 of the Accomplishment Instructions of
Boeing Special Attention Service Bulletin 737-32-1448, Revision 1,
dated May 29, 2015.
(k) Exception to Service Information Specification
Where paragraph 1.E., ``Compliance,'' of Boeing Special
Attention Service Bulletin 737-32-1448, Revision 1, dated May 29,
2015, specifies a compliance time ``from the original issue date on
this service bulletin,'' this AD requires compliance within the
specified compliance time ``after the effective date of this AD.''
(l) Credit for Previous Actions
This paragraph provides credit for the requirements of paragraph
(g) of this AD, if those actions were performed before the effective
date of this AD using Boeing Special Attention Service Bulletin 737-
32-1448, dated May 19, 2011, which is not incorporated by reference
in this AD.
(m) 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 (n)(1) of this AD.
Information may be emailed to: [email protected].
(2) Before using any approved AMOC, notify your appropriate
principal inspector, or lacking a principal inspector, the manager
of the local flight standards district office/certificate holding
district office.
(3) An AMOC that provides an acceptable level of safety may be
used for any repair, modification, or alteration required by this AD
if it is approved by the Boeing Commercial Airplanes Organization
Designation Authorization (ODA) that has been authorized by the
Manager, 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.
(n) Related Information
(1) For more information about this AD, contact Alan Pohl,
Aerospace Engineer, Airframe Branch, ANM-120S, FAA Seattle Aircraft
Certification Office, 1601 Lind Avenue SW., Renton, WA 98057-3356;
phone: 425-917-6450; fax: 425-917-6590; email: [email protected].
(2) Service information identified in this AD that is not
incorporated by reference is available at the addresses specified in
paragraphs (o)(3) and (o)(4) of this AD.
(o) 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 Special Attention Service Bulletin 737-32-1448,
Revision 1, dated May 29, 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 18, 2016.
Dorr M. Anderson,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2016-20686 Filed 8-30-16; 8:45 am]
BILLING CODE 4910-13-P