Airworthiness Directives; The Boeing Company Airplanes, 13840-13843 [2019-06792]
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Federal Register / Vol. 84, No. 67 / Monday, April 8, 2019 / Proposed Rules
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by § 25.143(a), and in addition to the
requirements of § 25.143(a) and in the
absence of other limiting factors, the
following special conditions are proposed
based on § 25.333(b):
a. The positive limiting load factor must
not be less than:
(1) 2.5g for the normal state of the
electronic flight control system with the high
lift devices retracted up to Vmo/Mmo. The
positive limiting load factor may be gradually
reduced down to 2.25g above Vmo/Mmo.
(2) 2.0g for the normal state of the
electronic flight control system with the high
lift devices extended.
b. The negative limiting load factor must be
equal to or more negative than:
(1) Minus 1.0g for the normal state of the
electronic flight control system with the high
lift devices retracted.
(2) 0.0g for the normal state of the
electronic flight control system with high lift
devices extended.
c. Maximum reachable positive load factor
wings level may be limited by the
characteristics of the electronic flight control
system or flight envelope protections (other
than load factor protection) provided that:
(1) The required values are readily
achievable in turns, and
(2) Wings level pitch up responsiveness is
satisfactory.
d. Maximum achievable negative load
factor may be limited by the characteristics
of the electronic flight control system or
flight envelope protections (other than load
factor protection) provided that:
(1) Pitch down responsiveness is
satisfactory, and
(2) From level flight, 0g is readily
achievable or alternatively, a satisfactory
trajectory change is readily achievable at
operational speeds. For the FAA to consider
a trajectory change as satisfactory, the
applicant should propose and justify a pitch
rate that provides sufficient maneuvering
capability in the most critical scenarios.
e. Compliance demonstration with the
above requirements may be performed
without ice accretion on the airframe.
f. These special conditions do not impose
an upper bound for the normal load factor
limit, nor does it require that the limiter
exist. If the limit is set at a value beyond the
structural design limit maneuvering load
factor ‘‘n’’ of §§ 25.333(b), 25.337(b) and
25.337(c), there should be a very obvious
positive tactile feel built into the controller
so that it serves as a deterrent to
inadvertently exceeding the structural limit.
Issued in Des Moines, Washington.
Suzanne Masterson,
Acting Manager, Transport Standards
Branch, Policy and Innovation Division,
Aircraft Certification Service.
[FR Doc. 2019–06647 Filed 4–5–19; 8:45 am]
BILLING CODE 4910–13–P
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2019–0188; Product
Identifier 2018–NM–174–AD]
RIN 2120–AA64
Airworthiness Directives; The Boeing
Company Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
We propose to adopt a new
airworthiness directive (AD) for all The
Boeing Company Model 747–200B, 747–
200C, 747–200F, 747–300, 747–400,
747–400D, 747–400F, 747–8F, and 747–
8 series airplanes. This AD was
prompted by reports of uncommanded
movement of the Captain’s and First
Officer’s seats. This proposed AD would
require, for the Captain’s and First
Officer’s seats, repetitive horizontal
actuator identifications, repetitive
checks of the horizontal movement
system (HMS), a detailed inspection of
the HMS for certain airplanes, and
applicable on-condition actions. This
proposed AD would also require an
inspection to determine the part number
and, if applicable, the serial number of
the Captain’s and First Officer’s seats
and applicable on-condition actions.
This proposed AD would also provide
an optional terminating action for the
repetitive checks of the HMS for certain
airplanes. We are proposing this AD to
address the unsafe condition on these
products.
SUMMARY:
We must receive comments on
this proposed AD by May 23, 2019.
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
https://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: Deliver to Mail
address above between 9 a.m. and 5
p.m., Monday through Friday, except
Federal holidays.
For service information identified in
this NPRM, contact Boeing Commercial
Airplanes, Attention: Contractual & Data
Services (C&DS), 2600 Westminster
Blvd., MC 110–SK57, Seal Beach, CA
DATES:
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90740–5600; telephone 562–797–1717;
internet https://
www.myboeingfleet.com. You may view
this service information at the FAA,
Transport Standards Branch, 2200
South 216th St., Des Moines, WA. For
information on the availability of this
material at the FAA, call 206–231–3195.
It is also available on the internet at
https://www.regulations.gov by searching
for and locating Docket No. FAA–2019–
0188.
Examining the AD Docket
You may examine the AD docket on
the internet at https://
www.regulations.gov by searching for
and locating Docket No. FAA–2019–
0188; or in person at Docket Operations
between 9 a.m. and 5 p.m., Monday
through Friday, except Federal holidays.
The AD docket contains this NPRM, the
regulatory evaluation, any comments
received, and other information. The
street address for Docket Operations
(phone: 800–647–5527) is in the
ADDRESSES section. Comments will be
available in the AD docket shortly after
receipt.
FOR FURTHER INFORMATION CONTACT:
Brandon Lucero, Aerospace Engineer,
Cabin Safety and Environmental
Systems Section, FAA, Seattle ACO
Branch, 2200 South 216th St., Des
Moines, WA 98198; phone and fax: 206–
231–3569; email: Brandon.Lucero@
faa.gov.
SUPPLEMENTARY INFORMATION:
Comments Invited
We invite you to send any written
relevant data, views, or arguments about
this proposal. Send your comments to
an address listed under the ADDRESSES
section. Include ‘‘Docket No. FAA–
2019–0188; Product Identifier 2018–
NM–174–AD’’ at the beginning of your
comments. We specifically invite
comments on the overall regulatory,
economic, environmental, and energy
aspects of this NPRM. We will consider
all comments received by the closing
date and may amend this NPRM
because of those comments.
We will post all comments we
receive, without change, to https://
www.regulations.gov, including any
personal information you provide. We
will also post a report summarizing each
substantive verbal contact we receive
about this proposed AD.
Discussion
We have received reports of
uncommanded movement of the
Captain’s and First Officer’s seats. An
operator reported that during a takeoff,
the First Officer’s seat unlocked from its
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Federal Register / Vol. 84, No. 67 / Monday, April 8, 2019 / Proposed Rules
seat tracks and moved aft. The First
Officer was unable to control the
airplane and the Captain took over the
controls to avoid a rejected takeoff. The
unlocking of the seat from the seat
tracks was caused by actuator damage,
which was a result of incorrect
adjustment of the seat’s manual release
lever cable, which allowed the clutch
mechanism to only partially engage.
In addition, one operator reported that
the Captain’s seat could not be locked
in position after the horizontal position
of the seat was adjusted in flight. The
seat became unlocked from the track
and moved freely forward and aft.
Control was given to the First Officer for
approach and landing. An inspection
found that the horizontal actuator
output shaft had broken. When a
horizontal actuator output shaft breaks,
the pilot cannot prevent seat movement
in a forward and aft direction and
cannot lock the seat in position. A
broken horizontal actuator output shaft
is the result of high loads that exceed
the design limits that are caused by a
stalled motor that can occur due to high
mechanical resistance to motion during
powered operation of the seat. Foreign
object debris (FOD) in the seat tracks is
another condition that can result in a
stalled motor and cause the horizontal
actuator output shaft to break.
This condition, if not addressed,
could result in uncommanded
movement of the Captain’s or First
Officer’s seat during a critical part of a
flight, such as takeoff or landing, and
could cause a flight control obstruction
or unintended flight control input,
which could lead to reduced
controllability of the airplane.
Related Service Information Under 1
CFR Part 51
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We reviewed Boeing Special
Attention Service Bulletin 747–25–
3644, Revision 1, dated July 17, 2018.
This service information describes
procedures for an inspection to
determine the part number, and, if
applicable, the serial number of the
Captain’s and First Officer’s seats and
applicable on-condition actions. Oncondition actions include an inspection
of each seat’s fore/aft and vertical
manual control levers for looseness;
moving the adjustment nut, tightening
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the lock nut, readjusting the control
lever, and doing a functional test; and
installing a serviceable seat.
We also reviewed Boeing Special
Attention Service Bulletin 747–25–
3653, Revision 1, dated October 19,
2018. This service information describes
procedures for repetitive horizontal
actuator identifications, repetitive
checks of the HMS, a detailed
inspection of the HMS, and applicable
on-condition actions. On-condition
actions include clearing the seat tracks
of FOD, an overhaul of the HMS, and
checks of the HMS. The service
information also describes procedures
for an optional terminating action for
the repetitive checks by installing a
serviceable Captain’s or First Officer’s
seat.
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 proposing 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.
Proposed AD Requirements
This proposed AD would require
accomplishment of the actions
identified in the Accomplishment
Instructions of Boeing Special Attention
Service Bulletin 747–25–3644, Revision
1, dated July 17, 2018, described
previously, except as discussed under
‘‘Differences Between this Proposed AD
and the Service Information,’’ and
except for any differences identified as
exceptions in the regulatory text of this
proposed AD.
This proposed AD would also require
accomplishment of the actions
identified as ‘‘RC’’ (required for
compliance) in the Accomplishment
Instructions of Boeing Special Attention
Service Bulletin 747–25–3653, Revision
1, dated October 19, 2018, described
previously except as discussed under
‘‘Differences Between this Proposed AD
and the Service Information,’’ and
except for any differences identified as
exceptions in the regulatory text of this
proposed AD.
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13841
For information on the procedures
and compliance times, see this service
information at https://
www.regulations.gov by searching for
and locating Docket No. FAA–2019–
0188.
Differences Between This Proposed AD
and the Service Information
Where Boeing Special Attention
Service Bulletin 747–25–3644, Revision
1, dated July 17, 2018, specifies to do
the actions within 72 months after the
original issue date of the service
bulletin, this proposed AD would
require accomplishment of those actions
within 36 months after the effective date
of this AD. The 36-month compliance
time corresponds with the compliance
time in Boeing Special Attention
Service Bulletin 747–25–3653, Revision
1, dated October 19, 2018. We have
determined a 36-month compliance
time is appropriate for doing the actions
specified in this proposed AD. We have
coordinated this difference with Boeing.
The effectivity of Boeing Special
Attention Service Bulletin 747–25–
3644, Revision 1, dated July 17, 2018;
and Boeing Special Attention Service
Bulletin 747–25–3653, Revision 1, dated
October 19, 2018, is limited to The
Boeing Company Model 747–200B, 747–
200C, 747–200F, 747–300, 747–400,
747–400D, 747–400F, 747–8F, and 747–
8 series airplanes equipped with Ipeco
part number series 3A090 and 3A258
Captain’s and First Officer’s powered
seats, line number 699 and on.
However, the applicability of this
proposed AD includes all The Boeing
Company Model 747–200B, 747–200C,
747–200F, 747–300, 747–400, 747–
400D, 747–400F, 747–8F, and 747–8
series airplanes. Because the affected
parts are rotable parts, we have
determined that these parts could later
be installed on airplanes that were
initially delivered with acceptable parts,
thereby subjecting those airplanes to the
unsafe condition. This difference has
been coordinated with Boeing.
Costs of Compliance
We estimate that this proposed AD
affects 95 airplanes of U.S. registry. We
estimate the following costs to comply
with this proposed AD:
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Federal Register / Vol. 84, No. 67 / Monday, April 8, 2019 / Proposed Rules
ESTIMATED COSTS FOR REQUIRED ACTIONS
Labor cost
Seat identification (part and serial number).
Detailed inspection, horizontal movement system.
Checks, horizontal movement system ...
1 work-hour × $85 per hour = $85 ........
$0
$85 .........................
$8,075 per seat.
1 work-hour × $85 per hour = $85, per
seat.
2 work-hour × $85 per hour = $170 per
seat, per check cycle.
0
$85 per seat ...........
$8,075 per seat.
0
$170 per seat, per
check cycle.
$16,150 per seat,
per check cycle.
We estimate the following costs to do
any necessary on-condition actions that
would be required. We have no way of
Parts cost
Cost on U.S. operators
Action
Cost per product
determining the number of aircraft that
might need these on-condition actions:
ESTIMATED COSTS OF ON-CONDITION ACTIONS *
Action
Labor cost
Parts cost
Overhaul or replacement, horizontal
movement system.
Inspection of each seat’s fore/aft and
vertical manual control levers.
Installation of serviceable seats .............
Up to 15 work-hours × $85 per hour =
$1,275, per seat.
1 work-hour × $85 per hour = $85, per
seat.
1 work-hour × $85 per hour = $85, per
seat.
1 work-hour × $85 per hour = $85, per
seat.
1 work-hour × $85 per hour = $85, per
seat.
Up to $6,400 per seat ..........
Up to $7,675 per seat.
0 ............................................
$85 per seat.
0 ............................................
$85 per seat.
0 ............................................
$85 per seat.
0 ............................................
$85, per seat.
Clearing FOD .........................................
Functional test, adjusted control lever
cable.
Cost per product
* The estimated cost for tooling to align an affected seat for adjustment of the control lever cable is up to $46,064.
We have received no definitive data
that would enable us to provide cost
estimates for the optional terminating
action for the on-condition repetitive
checks specified in this proposed AD.
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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.
This proposed AD is issued in
accordance with authority delegated by
the Executive Director, Aircraft
Certification Service, as authorized by
FAA Order 8000.51C. In accordance
with that order, issuance of ADs is
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normally a function of the Compliance
and Airworthiness Division, but during
this transition period, the Executive
Director has delegated the authority to
issue ADs applicable to transport
category airplanes and associated
appliances to the Director of the System
Oversight Division.
Regulatory Findings
We have determined that this
proposed AD would not have federalism
implications under Executive Order
13132. This proposed AD would 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 the proposed regulation:
(1) Is not a ‘‘significant regulatory
action’’ under Executive Order 12866,
(2) Is not a ‘‘significant rule’’ under
the 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.
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List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation
safety, Incorporation by reference,
Safety.
The Proposed Amendment
Accordingly, under the authority
delegated to me by the Administrator,
the FAA proposes to amend 14 CFR part
39 as follows:
PART 39—AIRWORTHINESS
DIRECTIVES
1. The authority citation for part 39
continues to read as follows:
■
Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13
[Amended]
2. The FAA amends § 39.13 by adding
the following new airworthiness
directive (AD):
■
The Boeing Company: Docket No. FAA–
2019–0188; Product Identifier 2018–
NM–174–AD.
(a) Comments Due Date
The FAA must receive comments on this
AD action by May 23, 2019.
(b) Affected ADs
None.
(c) Applicability
This AD applies to all The Boeing
Company Model 747–200B, 747–200C, 747–
200F, 747–300, 747–400, 747–400D, 747–
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Federal Register / Vol. 84, No. 67 / Monday, April 8, 2019 / Proposed Rules
400F, 747–8F, and 747–8 series airplanes,
certificated in any category.
(k) Alternative Methods of Compliance
(AMOCs)
(d) Subject
Air Transport Association (ATA) of
America Code 25, Equipment/furnishings.
(1) The Manager, Seattle ACO Branch,
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
certification office, send it to the attention of
the person identified in paragraph (l)(1) of
this AD. Information may be emailed to: 9ANM-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
Branch, FAA, 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 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. If a step or substep is
labeled ‘‘RC Exempt,’’ then the RC
requirement is removed from that step or
substep. 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.
(e) Unsafe Condition
This AD was prompted by reports of
uncommanded movement of the Captain’s
and First Officer’s seats. We are issuing this
AD to address uncommanded movement of
the Captain’s and First Officer’s seats. An
uncommanded seat movement during a
critical part of a flight, such as takeoff or
landing, could cause a flight control
obstruction or unintended flight control
input, which could lead to reduced
controllability of the airplane.
(f) Compliance
Comply with this AD within the
compliance times specified, unless already
done.
(g) Horizontal Actuator Identification,
Detailed Inspection, and Repetitive Checks
of Horizontal Movement System and OnCondition Actions
Except as specified in paragraph (i) of this
AD: At the applicable times specified in
paragraph 1.E., ‘‘Compliance,’’ of Boeing
Special Attention Service Bulletin 747–25–
3653, Revision 1, dated October 19, 2018, do
all applicable actions identified as ‘‘RC’’
(required for compliance) in, and in
accordance with, the Accomplishment
Instructions of Boeing Special Attention
Service Bulletin 747–25–3653, Revision 1,
dated October 19, 2018.
(h) Seat Identification and On-Condition
Actions
Within 36 months after the effective date
of this AD, do an inspection of the nameplate
on the Captain’s and First Officer’s seats for
the part number, and serial number as
applicable, and do all applicable oncondition actions in accordance with the
Accomplishment Instructions of Boeing
Special Attention Service Bulletin 747–25–
3644, Revision 1, dated July 17, 2018. A
review of the airplane maintenance records
may be used for the seat inspection if the part
number and serial number can be
conclusively determined from that review.
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(i) Exceptions to Service Information
Specifications
For purposes of determining compliance
with the requirements of this AD: Where
Boeing Special Attention Service Bulletin
747–25–3653, Revision 1, dated October 19,
2018, uses the phrase ‘‘the original issue date
of this service bulletin,’’ this AD requires
using ‘‘the effective date of this AD.’’
(j) Terminating Action for Repetitive
Inspections
Installation of a serviceable Captain’s or
First Officer’s seat as specified in, and in
accordance with, the Accomplishment
Instructions of Boeing Special Attention
Service Bulletin 747–25–3653, Revision 1,
dated October 19, 2018, terminates the
repetitive inspections required by paragraph
(g) of this AD, for that seat only.
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(l) Related Information
(1) For more information about this AD,
contact Brandon Lucero, Aerospace Engineer,
Cabin Safety and Environmental Systems
Section, FAA, Seattle ACO Branch, 2200
South 216th St., Des Moines, WA 98198;
phone and fax: 206–231–3569; email:
Brandon.Lucero@faa.gov.
(2) For service information identified in
this AD, contact Boeing Commercial
Airplanes, Attention: Contractual & Data
Services (C&DS), 2600 Westminster Blvd.,
MC 110–SK57, Seal Beach, CA 90740–5600;
telephone 562–797–1717; internet https://
www.myboeingfleet.com. You may view this
referenced service information at the FAA,
Transport Standards Branch, 2200 South
216th St., Des Moines, WA. For information
on the availability of this material at the
FAA, call 206–231–3195.
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13843
Issued in Des Moines, Washington, on
April 1, 2019.
Michael Kaszycki,
Acting Director, System Oversight Division,
Aircraft Certification Service.
[FR Doc. 2019–06792 Filed 4–5–19; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2019–0193; Product
Identifier 2018–NM–159–AD]
RIN 2120–AA64
Airworthiness Directives; Airbus SAS
Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
We propose to supersede
Airworthiness Directive (AD) 2018–22–
13, which applies to certain Airbus SAS
Model A350–941 and –1041 airplanes.
AD 2018–22–13 requires revising the
airplane flight manual (AFM) to provide
the flightcrew with updated procedures
related to inboard aileron fault
operations. Since we issued AD 2018–
22–13, we have determined that
additional actions are necessary to
address the unsafe condition and that
additional airplanes are subject to the
unsafe condition. This proposed AD
would also require modifying the
electronic centralized aircraft
monitoring (ECAM) procedures by
installing an Airbus Temporary Quick
Change (ATQC) and activating an ECAM
temporary change (ETC). We are
proposing this AD to address the unsafe
condition on these products.
DATES: We must receive comments on
this proposed AD by May 23, 2019.
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
https://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: Deliver to Mail
address above between 9 a.m. and 5
p.m., Monday through Friday, except
Federal holidays.
For service information identified in
this NPRM, contact Airbus SAS,
SUMMARY:
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]]>Agencies
[Federal Register Volume 84, Number 67 (Monday, April 8, 2019)]
[Proposed Rules]
[Pages 13840-13843]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2019-06792]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2019-0188; Product Identifier 2018-NM-174-AD]
RIN 2120-AA64
Airworthiness Directives; The Boeing Company Airplanes
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking (NPRM).
-----------------------------------------------------------------------
SUMMARY: We propose to adopt a new airworthiness directive (AD) for all
The Boeing Company Model 747-200B, 747-200C, 747-200F, 747-300, 747-
400, 747-400D, 747-400F, 747-8F, and 747-8 series airplanes. This AD
was prompted by reports of uncommanded movement of the Captain's and
First Officer's seats. This proposed AD would require, for the
Captain's and First Officer's seats, repetitive horizontal actuator
identifications, repetitive checks of the horizontal movement system
(HMS), a detailed inspection of the HMS for certain airplanes, and
applicable on-condition actions. This proposed AD would also require an
inspection to determine the part number and, if applicable, the serial
number of the Captain's and First Officer's seats and applicable on-
condition actions. This proposed AD would also provide an optional
terminating action for the repetitive checks of the HMS for certain
airplanes. We are proposing this AD to address the unsafe condition on
these products.
DATES: We must receive comments on this proposed AD by May 23, 2019.
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 https://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: Deliver to Mail address above between 9
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
For service information identified in this NPRM, contact Boeing
Commercial Airplanes, Attention: Contractual & Data Services (C&DS),
2600 Westminster Blvd., MC 110-SK57, Seal Beach, CA 90740-5600;
telephone 562-797-1717; internet https://www.myboeingfleet.com. You may
view this service information at the FAA, Transport Standards Branch,
2200 South 216th St., Des Moines, WA. For information on the
availability of this material at the FAA, call 206-231-3195. It is also
available on the internet at https://www.regulations.gov by searching
for and locating Docket No. FAA-2019-0188.
Examining the AD Docket
You may examine the AD docket on the internet at https://www.regulations.gov by searching for and locating Docket No. FAA-2019-
0188; or in person at Docket Operations between 9 a.m. and 5 p.m.,
Monday through Friday, except Federal holidays. The AD docket contains
this NPRM, the regulatory evaluation, any comments received, and other
information. The street address for Docket Operations (phone: 800-647-
5527) is in the ADDRESSES section. Comments will be available in the AD
docket shortly after receipt.
FOR FURTHER INFORMATION CONTACT: Brandon Lucero, Aerospace Engineer,
Cabin Safety and Environmental Systems Section, FAA, Seattle ACO
Branch, 2200 South 216th St., Des Moines, WA 98198; phone and fax: 206-
231-3569; email: [email protected].
SUPPLEMENTARY INFORMATION:
Comments Invited
We invite you to send any written relevant data, views, or
arguments about this proposal. Send your comments to an address listed
under the ADDRESSES section. Include ``Docket No. FAA-2019-0188;
Product Identifier 2018-NM-174-AD'' at the beginning of your comments.
We specifically invite comments on the overall regulatory, economic,
environmental, and energy aspects of this NPRM. We will consider all
comments received by the closing date and may amend this NPRM because
of those comments.
We will post all comments we receive, without change, to https://www.regulations.gov, including any personal information you provide. We
will also post a report summarizing each substantive verbal contact we
receive about this proposed AD.
Discussion
We have received reports of uncommanded movement of the Captain's
and First Officer's seats. An operator reported that during a takeoff,
the First Officer's seat unlocked from its
[[Page 13841]]
seat tracks and moved aft. The First Officer was unable to control the
airplane and the Captain took over the controls to avoid a rejected
takeoff. The unlocking of the seat from the seat tracks was caused by
actuator damage, which was a result of incorrect adjustment of the
seat's manual release lever cable, which allowed the clutch mechanism
to only partially engage.
In addition, one operator reported that the Captain's seat could
not be locked in position after the horizontal position of the seat was
adjusted in flight. The seat became unlocked from the track and moved
freely forward and aft. Control was given to the First Officer for
approach and landing. An inspection found that the horizontal actuator
output shaft had broken. When a horizontal actuator output shaft
breaks, the pilot cannot prevent seat movement in a forward and aft
direction and cannot lock the seat in position. A broken horizontal
actuator output shaft is the result of high loads that exceed the
design limits that are caused by a stalled motor that can occur due to
high mechanical resistance to motion during powered operation of the
seat. Foreign object debris (FOD) in the seat tracks is another
condition that can result in a stalled motor and cause the horizontal
actuator output shaft to break.
This condition, if not addressed, could result in uncommanded
movement of the Captain's or First Officer's seat during a critical
part of a flight, such as takeoff or landing, and could cause a flight
control obstruction or unintended flight control input, which could
lead to reduced controllability of the airplane.
Related Service Information Under 1 CFR Part 51
We reviewed Boeing Special Attention Service Bulletin 747-25-3644,
Revision 1, dated July 17, 2018. This service information describes
procedures for an inspection to determine the part number, and, if
applicable, the serial number of the Captain's and First Officer's
seats and applicable on-condition actions. On-condition actions include
an inspection of each seat's fore/aft and vertical manual control
levers for looseness; moving the adjustment nut, tightening the lock
nut, readjusting the control lever, and doing a functional test; and
installing a serviceable seat.
We also reviewed Boeing Special Attention Service Bulletin 747-25-
3653, Revision 1, dated October 19, 2018. This service information
describes procedures for repetitive horizontal actuator
identifications, repetitive checks of the HMS, a detailed inspection of
the HMS, and applicable on-condition actions. On-condition actions
include clearing the seat tracks of FOD, an overhaul of the HMS, and
checks of the HMS. The service information also describes procedures
for an optional terminating action for the repetitive checks by
installing a serviceable Captain's or First Officer's seat.
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 proposing 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.
Proposed AD Requirements
This proposed AD would require accomplishment of the actions
identified in the Accomplishment Instructions of Boeing Special
Attention Service Bulletin 747-25-3644, Revision 1, dated July 17,
2018, described previously, except as discussed under ``Differences
Between this Proposed AD and the Service Information,'' and except for
any differences identified as exceptions in the regulatory text of this
proposed AD.
This proposed AD would also require accomplishment of the actions
identified as ``RC'' (required for compliance) in the Accomplishment
Instructions of Boeing Special Attention Service Bulletin 747-25-3653,
Revision 1, dated October 19, 2018, described previously except as
discussed under ``Differences Between this Proposed AD and the Service
Information,'' and except for any differences identified as exceptions
in the regulatory text of this proposed AD.
For information on the procedures and compliance times, see this
service information at https://www.regulations.gov by searching for and
locating Docket No. FAA-2019-0188.
Differences Between This Proposed AD and the Service Information
Where Boeing Special Attention Service Bulletin 747-25-3644,
Revision 1, dated July 17, 2018, specifies to do the actions within 72
months after the original issue date of the service bulletin, this
proposed AD would require accomplishment of those actions within 36
months after the effective date of this AD. The 36-month compliance
time corresponds with the compliance time in Boeing Special Attention
Service Bulletin 747-25-3653, Revision 1, dated October 19, 2018. We
have determined a 36-month compliance time is appropriate for doing the
actions specified in this proposed AD. We have coordinated this
difference with Boeing.
The effectivity of Boeing Special Attention Service Bulletin 747-
25-3644, Revision 1, dated July 17, 2018; and Boeing Special Attention
Service Bulletin 747-25-3653, Revision 1, dated October 19, 2018, is
limited to The Boeing Company Model 747-200B, 747-200C, 747-200F, 747-
300, 747-400, 747-400D, 747-400F, 747-8F, and 747-8 series airplanes
equipped with Ipeco part number series 3A090 and 3A258 Captain's and
First Officer's powered seats, line number 699 and on. However, the
applicability of this proposed AD includes all The Boeing Company Model
747-200B, 747-200C, 747-200F, 747-300, 747-400, 747-400D, 747-400F,
747-8F, and 747-8 series airplanes. Because the affected parts are
rotable parts, we have determined that these parts could later be
installed on airplanes that were initially delivered with acceptable
parts, thereby subjecting those airplanes to the unsafe condition. This
difference has been coordinated with Boeing.
Costs of Compliance
We estimate that this proposed AD affects 95 airplanes of U.S.
registry. We estimate the following costs to comply with this proposed
AD:
[[Page 13842]]
Estimated Costs for Required Actions
----------------------------------------------------------------------------------------------------------------
Cost on U.S.
Action Labor cost Parts cost Cost per product operators
----------------------------------------------------------------------------------------------------------------
Seat identification (part and 1 work-hour x $85 per $0 $85............... $8,075 per seat.
serial number). hour = $85.
Detailed inspection, horizontal 1 work-hour x $85 per 0 $85 per seat...... $8,075 per seat.
movement system. hour = $85, per seat.
Checks, horizontal movement 2 work-hour x $85 per 0 $170 per seat, per $16,150 per seat,
system. hour = $170 per seat, check cycle. per check cycle.
per check cycle.
----------------------------------------------------------------------------------------------------------------
We estimate the following costs to do any necessary on-condition
actions that would be required. We have no way of determining the
number of aircraft that might need these on-condition actions:
Estimated Costs of On-Condition Actions *
----------------------------------------------------------------------------------------------------------------
Action Labor cost Parts cost Cost per product
----------------------------------------------------------------------------------------------------------------
Overhaul or replacement, horizontal Up to 15 work-hours x $85 Up to $6,400 per seat. Up to $7,675 per seat.
movement system. per hour = $1,275, per
seat.
Inspection of each seat's fore/aft 1 work-hour x $85 per hour 0..................... $85 per seat.
and vertical manual control levers. = $85, per seat.
Installation of serviceable seats.. 1 work-hour x $85 per hour 0..................... $85 per seat.
= $85, per seat.
Clearing FOD....................... 1 work-hour x $85 per hour 0..................... $85 per seat.
= $85, per seat.
Functional test, adjusted control 1 work-hour x $85 per hour 0..................... $85, per seat.
lever cable. = $85, per seat.
----------------------------------------------------------------------------------------------------------------
* The estimated cost for tooling to align an affected seat for adjustment of the control lever cable is up to
$46,064.
We have received no definitive data that would enable us to provide
cost estimates for the optional terminating action for the on-condition
repetitive checks specified in this proposed 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.
This proposed AD is issued in accordance with authority delegated
by the Executive Director, Aircraft Certification Service, as
authorized by FAA Order 8000.51C. In accordance with that order,
issuance of ADs is normally a function of the Compliance and
Airworthiness Division, but during this transition period, the
Executive Director has delegated the authority to issue ADs applicable
to transport category airplanes and associated appliances to the
Director of the System Oversight Division.
Regulatory Findings
We have determined that this proposed AD would not have federalism
implications under Executive Order 13132. This proposed AD would 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 the proposed
regulation:
(1) Is not a ``significant regulatory action'' under Executive
Order 12866,
(2) Is not a ``significant rule'' under the 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.
The Proposed Amendment
Accordingly, under the authority delegated to me by the
Administrator, the FAA proposes to amend 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):
The Boeing Company: Docket No. FAA-2019-0188; Product Identifier
2018-NM-174-AD.
(a) Comments Due Date
The FAA must receive comments on this AD action by May 23, 2019.
(b) Affected ADs
None.
(c) Applicability
This AD applies to all The Boeing Company Model 747-200B, 747-
200C, 747-200F, 747-300, 747-400, 747-400D, 747-
[[Page 13843]]
400F, 747-8F, and 747-8 series airplanes, certificated in any
category.
(d) Subject
Air Transport Association (ATA) of America Code 25, Equipment/
furnishings.
(e) Unsafe Condition
This AD was prompted by reports of uncommanded movement of the
Captain's and First Officer's seats. We are issuing this AD to
address uncommanded movement of the Captain's and First Officer's
seats. An uncommanded seat movement during a critical part of a
flight, such as takeoff or landing, could cause a flight control
obstruction or unintended flight control input, which could lead to
reduced controllability of the airplane.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(g) Horizontal Actuator Identification, Detailed Inspection, and
Repetitive Checks of Horizontal Movement System and On-Condition
Actions
Except as specified in paragraph (i) of this AD: At the
applicable times specified in paragraph 1.E., ``Compliance,'' of
Boeing Special Attention Service Bulletin 747-25-3653, Revision 1,
dated October 19, 2018, do all applicable actions identified as
``RC'' (required for compliance) in, and in accordance with, the
Accomplishment Instructions of Boeing Special Attention Service
Bulletin 747-25-3653, Revision 1, dated October 19, 2018.
(h) Seat Identification and On-Condition Actions
Within 36 months after the effective date of this AD, do an
inspection of the nameplate on the Captain's and First Officer's
seats for the part number, and serial number as applicable, and do
all applicable on-condition actions in accordance with the
Accomplishment Instructions of Boeing Special Attention Service
Bulletin 747-25-3644, Revision 1, dated July 17, 2018. A review of
the airplane maintenance records may be used for the seat inspection
if the part number and serial number can be conclusively determined
from that review.
(i) Exceptions to Service Information Specifications
For purposes of determining compliance with the requirements of
this AD: Where Boeing Special Attention Service Bulletin 747-25-
3653, Revision 1, dated October 19, 2018, uses the phrase ``the
original issue date of this service bulletin,'' this AD requires
using ``the effective date of this AD.''
(j) Terminating Action for Repetitive Inspections
Installation of a serviceable Captain's or First Officer's seat
as specified in, and in accordance with, the Accomplishment
Instructions of Boeing Special Attention Service Bulletin 747-25-
3653, Revision 1, dated October 19, 2018, terminates the repetitive
inspections required by paragraph (g) of this AD, for that seat
only.
(k) Alternative Methods of Compliance (AMOCs)
(1) The Manager, Seattle ACO Branch, 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 certification office, send it to the attention of the
person identified in paragraph (l)(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 Branch, FAA, 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 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. If a step or substep is labeled ``RC Exempt,'' then the
RC requirement is removed from that step or substep. 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
(1) For more information about this AD, contact Brandon Lucero,
Aerospace Engineer, Cabin Safety and Environmental Systems Section,
FAA, Seattle ACO Branch, 2200 South 216th St., Des Moines, WA 98198;
phone and fax: 206-231-3569; email: [email protected].
(2) For service information identified in this AD, contact
Boeing Commercial Airplanes, Attention: Contractual & Data Services
(C&DS), 2600 Westminster Blvd., MC 110-SK57, Seal Beach, CA 90740-
5600; telephone 562-797-1717; internet https://www.myboeingfleet.com. You may view this referenced service
information at the FAA, Transport Standards Branch, 2200 South 216th
St., Des Moines, WA. For information on the availability of this
material at the FAA, call 206-231-3195.
Issued in Des Moines, Washington, on April 1, 2019.
Michael Kaszycki,
Acting Director, System Oversight Division, Aircraft Certification
Service.
[FR Doc. 2019-06792 Filed 4-5-19; 8:45 am]
BILLING CODE 4910-13-P
