Airworthiness Directives; The Boeing Company Airplanes, 60351-60354 [2019-24329]
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Federal Register / Vol. 84, No. 217 / Friday, November 8, 2019 / Proposed Rules
2. Will not affect intrastate aviation in
Alaska, and
3. 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.
The FAA prepared an economic
evaluation of the estimated costs to
comply with this proposed AD and
placed it in the AD docket.
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):
■
Airbus Helicopters: Docket No. FAA–2019–
0882; Product Identifier 2018–SW–113–
AD.
(a) Applicability
This AD applies to Airbus Helicopters
Model AS332C, AS332C1, AS332L, and
AS332L1 helicopters, certificated in any
category, delivered to the first owner or
customer before September 1, 2018, and with
attachment screws part number (P/N)
330A22013520 installed with main gearbox
(MGB) right hand (RH) side rear attachment
fitting P/N 330A22270207 and left hand (LH)
side rear attachment fitting P/N
330A22270206 of the MGB suspension bars.
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(b) Unsafe Condition
This AD defines the unsafe condition as
elongation of the attachment screws and loss
of tightening torque of the nut. This
condition could result in structural failure of
an MGB attachment fitting, detachment of an
MGB suspension bar, and subsequent loss of
control of the helicopter.
(c) Comments Due Date
The FAA must receive comments by
January 7, 2020.
(d) Compliance
You are responsible for performing each
action required by this AD within the
specified compliance time unless it has
already been accomplished prior to that time.
(e) Required Actions
Within 110 hours time-in-service, remove
the sealing compound and inspect each
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screw on the RH and LH rear attachment
fitting by identifying the number of threads
‘‘F’’ that extend beyond the nut as shown in
Detail ‘‘B’’ of Figure 2 of Airbus Helicopter
Alert Service Bulletin No. AS332–53.02.04,
Revision 0, dated November 21, 2018 (ASB
AS332–53.02.04).
(1) If there are 2 or less threads on each of
the four screws; or there are 3 or more
threads on any screw with a thread height
‘‘H’’ less than 5 mm (0.196 in), before further
flight, apply a sealing compound on the nuts,
and convex and concave washers.
(2) If there are 3 or more threads on any
screw with a thread height ‘‘H’’ of 5 mm
(0.196 in) or more, before further flight, do
the following, and for more than one screw,
do one at a time while working in a cross
pattern: Remove from service the nut; and
remove the screw from the helicopter and
measure the length ‘‘L’’ of the screw as
shown in Detail ‘‘D’’ of Figure 2 of ASB
AS332–53.02.04.
(i) If any washers are bent or corroded,
before further flight, remove from service the
washers.
(ii) If the length ‘‘L’’ measurement is less
than or equal to 59.3 mm (2.334 in) for each
screw removed as required by paragraph
(e)(2) of this AD, visually inspect the screw
for corrosion and cracks.
(A) For each screw with corrosion or a
crack, before further flight, replace the screw
with an airworthy screw.
(B) For any screw with no corrosion or
cracks, before further flight, re-install the
screw and washers. Install a new nut and
apply sealant.
(iii) If the length ‘‘L’’ measurement is
greater than 59.3 mm (2.334 in) for any screw
removed as required by paragraph (e)(2) of
this AD, before further flight, replace the rear
attachment fitting that the screw was
removed from and its set of four screws,
washers, and nuts, and apply sealant as
shown in Figures 2 and 3 of ASB AS332–
53.02.04.
(f) Alternative Methods of Compliance
(AMOCs)
(1) The Manager, Safety Management
Section, Rotorcraft Standards Branch, FAA,
may approve AMOCs for this AD. Send your
proposal to: Matt Fuller, Senior Aviation
Safety Engineer, Safety Management Section,
Rotorcraft Standards Branch, FAA, 10101
Hillwood Pkwy., Fort Worth, TX 76177;
telephone (817) 222–5110; email 9-ASWFTW-AMOC-Requests@faa.gov.
(2) For operations conducted under a 14
CFR part 119 operating certificate or under
14 CFR part 91, subpart K, the FAA suggests
that you notify your principal inspector, or
lacking a principal inspector, the manager of
the local flight standards district office or
certificate holding district office before
operating any aircraft complying with this
AD through an AMOC.
(g) Additional Information
The subject of this AD is addressed in
European Aviation Safety Agency (EASA) AD
No. 2018–0282, dated December 19, 2018.
You may view the EASA AD on the internet
at https://www.regulations.gov in the AD
Docket.
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60351
(h) Subject
Joint Aircraft Service Component (JASC)
Code: 6320, Main Rotor Gearbox.
Issued in Fort Worth, Texas, on October 31,
2019.
Helene T. Gandy,
Acting Director, Compliance & Airworthiness
Division, Aircraft Certification Service.
[FR Doc. 2019–24342 Filed 11–7–19; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2019–0859; Product
Identifier 2019–NM–114–AD]
RIN 2120–AA64
Airworthiness Directives; The Boeing
Company Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
The FAA proposes to adopt a
new airworthiness directive (AD) for
certain The Boeing Company Model
747–100, 747–100B, 747–100B SUD,
747–200B, 747–200C, 747–200F, 747–
300, 747–400, 747–400D, 747–400F,
747SR, and 747SP series airplanes. This
proposed AD results from fuel system
reviews conducted by the manufacturer.
This proposed AD would require
replacement of the bonding jumpers on
the auxiliary power unit (APU) fuel
pump. This proposed AD would also
require, for certain airplanes,
installation of a second bonding jumper;
an inspection of the override/jettison
fuel pumps and transfer/jettison fuel
pumps to determine if the bonding
jumper has a one-piece braid or twopiece braid and replacement of the
bonding jumper if necessary; and
replacement of the bonding jumper on
the electrical scavenge fuel pump. The
FAA is proposing this AD to address the
unsafe condition on these products.
DATES: The FAA must receive comments
on this proposed AD by December 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–
SUMMARY:
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Federal Register / Vol. 84, No. 217 / Friday, November 8, 2019 / Proposed Rules
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–2019–0859.
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–
0859; 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 is
listed above. Comments will be
available in the AD docket shortly after
receipt.
FOR FURTHER INFORMATION CONTACT:
Jeffrey Rothman, Aerospace Engineer,
Propulsion Section, FAA, Seattle ACO
Branch, 2200 South 216th St., Des
Moines, WA 98198; phone and fax: 206–
231–3558; email: jeffrey.rothman@
faa.gov.
SUPPLEMENTARY INFORMATION:
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Comments Invited
The FAA invites 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–2019–0859; Product
Identifier 2019–NM–114–AD’’ at the
beginning of your comments. The FAA
specifically invites comments on the
overall regulatory, economic,
environmental, and energy aspects of
this NPRM. The FAA will consider all
comments received by the closing date
and may amend this NPRM because of
those comments.
The FAA will post all comments
received, without change, to https://
www.regulations.gov, including any
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personal information you provide. The
FAA will also post a report
summarizing each substantive verbal
contact received about this NPRM.
Discussion
The FAA has examined the
underlying safety issues involved in fuel
tank explosions on several large
transport airplanes, including the
adequacy of existing regulations, the
service history of airplanes subject to
those regulations, and existing
maintenance practices for fuel tank
systems. As a result of those findings,
the FAA issued a final rule titled
‘‘Transport Airplane Fuel Tank System
Design Review, Flammability
Reduction, and Maintenance and
Inspection Requirements’’ (66 FR 23086,
May 7, 2001). In addition to new
airworthiness standards for transport
airplanes and new maintenance
requirements, that rule included
Amendment 21–78, which established
Special Federal Aviation Regulation No.
88 (‘‘SFAR 88’’) at 14 CFR part 21.
Subsequently, SFAR 88 was amended
by Amendment 21–82 (67 FR 57490,
September 10, 2002; corrected at 67 FR
70809, November 26, 2002) and
Amendment 21–83 (67 FR 72830,
December 9, 2002; corrected at 68 FR
37735, June 25, 2003, to change ‘‘21–82’’
to ‘‘21–83’’).
Among other actions, SFAR 88
requires certain type design (i.e., type
certificate (TC) and supplemental type
certificate (STC)) holders to substantiate
that their fuel tank systems can prevent
ignition sources in the fuel tanks. This
requirement applies to type design
holders for large turbine-powered
transport airplanes and for subsequent
modifications to those airplanes. It
requires them to perform design reviews
and to develop design changes and
maintenance procedures if their designs
do not meet the new fuel tank safety
standards. As explained in the preamble
to the final rule published on May 7,
2001, the FAA intended to adopt
airworthiness directives to mandate any
changes found necessary to address
unsafe conditions identified as a result
of these reviews.
In evaluating these design reviews,
the FAA has established four criteria
intended to define the unsafe conditions
associated with fuel tank systems that
require corrective actions. The
percentage of operating time during
which fuel tanks are exposed to
flammable conditions is one of these
criteria. The other three criteria address
the failure types under evaluation:
Single failures, single failures in
combination with another latent
condition(s), and in-service failure
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experience. For all four criteria, the
evaluations included consideration of
previous actions taken that may mitigate
the need for further action.
The FAA has determined that the
actions identified in this proposed AD
are necessary to reduce the potential of
ignition sources inside fuel tanks,
which, in combination with flammable
fuel vapors, could result in fuel tank
explosions and consequent loss of the
airplane.
The FAA has received data from the
fuel tank inspection program indicating
that the existing bond path design
provides insufficient bond resistance
margin between the fuel pump motor/
impeller and structure. In the event of
a fuel pump electrical fault, this
condition might cause arcs at the
existing fuel pump/tank interfaces and
an ignition of fuel vapor in the wing fuel
tank, which could result in a fuel tank
explosion.
Related Service Information Under 1
CFR Part 51
The FAA reviewed Boeing Service
Bulletin 747–28–2228, Revision 1, dated
September 27, 2001. This service
information describes procedures for a
replacement of the bonding jumpers on
the APU fuel pump; an inspection of the
six override/jettison fuel pumps and of
the two transfer/jettison fuel pumps to
determine if the bonding jumper has a
one-piece braid or two-piece braid, and
replacement of the existing bonding
jumper if the bonding jumper has a onepiece braid; installation of a second
bonding jumper; and replacement of the
bonding jumper on the electrical
scavenge fuel pump.
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.
Other Relevant Rulemaking
Boeing Service Bulletin 747–28–2228,
Revision 1, dated September 27, 2001,
identifies ‘‘Boeing Service Bulletin 747–
28–2033’’ as a concurrent requirement
for certain airplanes. Boeing Alert
Service Bulletin 747–28A2033, Revision
1, dated December 18, 2003, is the
appropriate source of service
information for accomplishing the
installation required by AD 2005–01–07,
Amendment 39–13931 (70 FR 1336,
January 7, 2005) (‘‘AD 2005–01–07’’).
The compliance time for accomplishing
the installation required by AD 2005–
01–07 has already passed; therefore, it is
not necessary to include Boeing Alert
Service Bulletin 747–28A2033 as a
concurrent requirement in this proposed
AD. The FAA issued AD 2005–01–07 to
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Federal Register / Vol. 84, No. 217 / Friday, November 8, 2019 / Proposed Rules
ensure adequate electrical bonding
between the housing of each fuel pump
and airplane structure outside the fuel
tanks. Inadequate electrical bonding, in
the event of a lightning strike or fuel
pump electrical fault, could cause
electrical arcing and ignition of fuel
vapor in the wing fuel tank, which
could result in a fuel tank explosion.
FAA’s Determination
Proposed AD Requirements
The FAA is proposing this AD
because the agency 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.
This proposed AD would require
accomplishing the actions specified in
the service information described
previously.
Costs of Compliance
The FAA estimates that this proposed
AD affects 74 airplanes of U.S. registry.
The FAA estimates the following costs
to comply with this proposed AD:
ESTIMATED COSTS
Labor cost
Parts cost
Cost per
product
Up to 15 work-hours × $85
per hour = Up to $1,275.
Up to $2,000 .....................
Up to $3,275 .....................
Action
Replacement, Installation,
and Inspection.
The FAA estimates the following
costs to do any necessary replacements
that would be required based on the
results of the proposed inspection. The
FAA has no way of determining the
Cost on U.S.
operators
Up to $242,350.
number of aircraft that might need these
replacements:
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ON-CONDITION COSTS
Action
Labor cost
Parts cost
Replacement ..................................
Up to 6 work-hours × $85 per
hour = Up to $510.
Up to $950 ....................................
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.
The FAA is 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
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Cost per product
Up to $1,460.
appliances to the Director of the System
Oversight Division.
PART 39—AIRWORTHINESS
DIRECTIVES
Regulatory Findings
■
The FAA 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 this proposed regulation:
(1) Is not a ‘‘significant regulatory
action’’ under Executive Order 12866,
(2) Will not affect intrastate aviation
in Alaska, and
(3) 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.
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–
2019–0859; Product Identifier 2019–
NM–114–AD.
(a) Comments Due Date
The FAA must receive comments by
December 23, 2019.
(b) Affected ADs
None.
(c) Applicability
This AD applies to The Boeing Company
Model 747–100, 747–100B, 747–100B SUD,
747–200B, 747–200C, 747–200F, 747–300,
747–400, 747–400D, 747–400F, 747SR, and
747SP series airplanes, certificated in any
category, line numbers (L/Ns) 1 through 1229
inclusive.
The Proposed Amendment
(d) Subject
Air Transport Association (ATA) of
America Code 28, Fuel.
Accordingly, under the authority
delegated to me by the Administrator,
the FAA proposes to amend 14 CFR part
39 as follows:
(e) Unsafe Condition
This AD was prompted by fuel system
reviews conducted by the manufacturer
indicating that the existing bond path design
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Federal Register / Vol. 84, No. 217 / Friday, November 8, 2019 / Proposed Rules
provides insufficient bond resistance margin
between the fuel pump motor/impeller and
structure. The FAA is issuing this AD to
address insufficient bond resistance margin
between the fuel pump motor/impeller and
structure. In the event of a fuel pump
electrical fault, this condition might cause
arcs at the existing fuel pump/tank interfaces
and an ignition of fuel vapor in the wing fuel
tank, which could result in a fuel tank
explosion and consequent loss of the
airplane.
(f) Compliance
Comply with this AD within the
compliance times specified, unless already
done.
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(g) Definitions
For the purposes of this AD, the definitions
specified in paragraphs (g)(1) through (4) of
this AD apply.
(1) Group 1 airplanes: L/Ns 1 through 167
inclusive.
(2) Group 2 airplanes: L/Ns 168 through
971 inclusive.
(3) Group 3 airplanes: L/Ns 972 through
1161 inclusive.
(4) Group 4 airplanes: L/Ns 1162 through
1229 inclusive.
(h) Replacement, Installation, and
Inspection
Within 60 months after the effective date
of this AD, do the applicable actions
specified in paragraphs (h)(1) through (4) of
this AD, in accordance with the
Accomplishment Instructions of Boeing
Service Bulletin 747–28–2228, Revision 1,
dated September 27, 2001.
(1) For Groups 1, 2, and 3 airplanes: Do the
actions specified in paragraphs (h)(1)(i) and
(ii) of this AD.
(i) Do a general visual inspection of the six
override/jettison fuel pumps to determine if
the bonding jumper has a one-piece braid or
two-piece braid. If the bonding jumper has a
one-piece braid, within 60 months after the
effective date of this AD, replace the existing
bonding jumper.
(ii) Install a second bonding jumper.
(2) For Groups 1, 2 and 3 airplanes with
horizontal stabilizer fuel tanks: Do the
actions specified in paragraphs (h)(2)(i) and
(ii) of this AD.
(i) Do a general visual inspection of the two
transfer/jettison fuel pumps to determine if
the bonding jumper has a one-piece braid or
a two-piece braid. If the bonding jumper has
a one-piece braid, within 60 months after the
effective date of this AD, replace the existing
bonding jumper.
(ii) Install a second bonding jumper.
(3) For all airplanes: Replace the bonding
jumpers on the auxiliary power unit (APU)
fuel pump.
(4) For Groups 1 and 2 airplanes: Replace
the bonding jumper on the electrical
scavenge fuel pump.
(i) 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
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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 (j)(1) 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 Company
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.
(j) Related Information
(1) For more information about this AD,
contact Jeffrey Rothman, Aerospace Engineer,
Propulsion Section, FAA, Seattle ACO
Branch, 2200 South 216th St., Des Moines,
WA 98198; phone and fax: 206–231–3558;
email: jeffrey.rothman@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
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
October 29, 2019.
Dionne Palermo,
Acting Director, System Oversight Division,
Aircraft Certification Service.
[FR Doc. 2019–24329 Filed 11–7–19; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 71
[Docket No. FAA–2019–0785; Airspace
Docket No. 19–AEA–14]
Proposed Revocation of Class E
Airspace; Grundy, VA
Federal Aviation
Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
This action proposes to
remove Class E airspace at Grundy, VA,
as Grundy Municipal Airport has been
abandoned, and controlled airspace is
SUMMARY:
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no longer required. This action would
enhance the safety and management of
controlled airspace within the national
airspace system.
DATES: Comments must be received on
or before December 23, 2019.
ADDRESSES: Send comments on this rule
to: U.S. Department of Transportation,
Docket Operations, 1200 New Jersey
Avenue SE, West Building Ground
Floor, Room W12–140, Washington, DC
20590; Telephone: (800) 647–5527, or
(202) 366–9826.You must identify the
Docket No. FAA–2019–0785; Airspace
Docket No. 19–AEA–14, at the
beginning of your comments. You may
also submit comments through the
internet at https://www.regulations.gov.
You may review the public docket
containing the proposal, any comments
received, and any final disposition in
person in the Dockets Office between
9:00 a.m. and 5:00 p.m., Monday
through Friday, except federal holidays.
FAA Order 7400.11D, Airspace
Designations and Reporting Points, and
subsequent amendments can be viewed
on line at https://www.faa.gov/air_
traffic/publications/. For further
information, you can contact the
Airspace Policy Group, Federal Aviation
Administration, 800 Independence
Avenue, SW, Washington, DC, 20591;
telephone: 202–267–8783. The Order is
also available for inspection at the
National Archives and Records
Administration (NARA). For
information on the availability of FAA
Order 7400.11D at NARA, email
fedreg.legal@nara.gov or go to https://
www.archives.gov/federal-register/cfr/
ibr-locations.html.
FOR FURTHER INFORMATION CONTACT: John
Fornito, Operations Support Group,
Eastern Service Center, Federal Aviation
Administration, 1701 Columbia Ave,
College Park, GA 30337; telephone (404)
305–6364.
SUPPLEMENTARY INFORMATION:
Authority for This Rulemaking
The FAA’s authority to issue rules
regarding aviation safety is found in
Title 49 of the United States Code.
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. This proposed
rulemaking is promulgated under the
authority described in Subtitle VII, part
A, Subpart I, Section 40103. Under that
section, the FAA is charged with
prescribing regulations to assign the use
of airspace necessary to ensure the
safety of aircraft and the efficient use of
airspace. This regulation is within the
scope of that authority as it would
E:\FR\FM\08NOP1.SGM
08NOP1
]]>Agencies
[Federal Register Volume 84, Number 217 (Friday, November 8, 2019)]
[Proposed Rules]
[Pages 60351-60354]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2019-24329]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2019-0859; Product Identifier 2019-NM-114-AD]
RIN 2120-AA64
Airworthiness Directives; The Boeing Company Airplanes
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking (NPRM).
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SUMMARY: The FAA proposes to adopt a new airworthiness directive (AD)
for certain The Boeing Company Model 747-100, 747-100B, 747-100B SUD,
747-200B, 747-200C, 747-200F, 747-300, 747-400, 747-400D, 747-400F,
747SR, and 747SP series airplanes. This proposed AD results from fuel
system reviews conducted by the manufacturer. This proposed AD would
require replacement of the bonding jumpers on the auxiliary power unit
(APU) fuel pump. This proposed AD would also require, for certain
airplanes, installation of a second bonding jumper; an inspection of
the override/jettison fuel pumps and transfer/jettison fuel pumps to
determine if the bonding jumper has a one-piece braid or two-piece
braid and replacement of the bonding jumper if necessary; and
replacement of the bonding jumper on the electrical scavenge fuel pump.
The FAA is proposing this AD to address the unsafe condition on these
products.
DATES: The FAA must receive comments on this proposed AD by December
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-
[[Page 60352]]
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-2019-0859.
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-
0859; 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 is listed above.
Comments will be available in the AD docket shortly after receipt.
FOR FURTHER INFORMATION CONTACT: Jeffrey Rothman, Aerospace Engineer,
Propulsion Section, FAA, Seattle ACO Branch, 2200 South 216th St., Des
Moines, WA 98198; phone and fax: 206-231-3558; email:
[email protected].
SUPPLEMENTARY INFORMATION:
Comments Invited
The FAA invites 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-2019-0859;
Product Identifier 2019-NM-114-AD'' at the beginning of your comments.
The FAA specifically invites comments on the overall regulatory,
economic, environmental, and energy aspects of this NPRM. The FAA will
consider all comments received by the closing date and may amend this
NPRM because of those comments.
The FAA will post all comments received, without change, to https://www.regulations.gov, including any personal information you provide.
The FAA will also post a report summarizing each substantive verbal
contact received about this NPRM.
Discussion
The FAA has examined the underlying safety issues involved in fuel
tank explosions on several large transport airplanes, including the
adequacy of existing regulations, the service history of airplanes
subject to those regulations, and existing maintenance practices for
fuel tank systems. As a result of those findings, the FAA issued a
final rule titled ``Transport Airplane Fuel Tank System Design Review,
Flammability Reduction, and Maintenance and Inspection Requirements''
(66 FR 23086, May 7, 2001). In addition to new airworthiness standards
for transport airplanes and new maintenance requirements, that rule
included Amendment 21-78, which established Special Federal Aviation
Regulation No. 88 (``SFAR 88'') at 14 CFR part 21. Subsequently, SFAR
88 was amended by Amendment 21-82 (67 FR 57490, September 10, 2002;
corrected at 67 FR 70809, November 26, 2002) and Amendment 21-83 (67 FR
72830, December 9, 2002; corrected at 68 FR 37735, June 25, 2003, to
change ``21-82'' to ``21-83'').
Among other actions, SFAR 88 requires certain type design (i.e.,
type certificate (TC) and supplemental type certificate (STC)) holders
to substantiate that their fuel tank systems can prevent ignition
sources in the fuel tanks. This requirement applies to type design
holders for large turbine-powered transport airplanes and for
subsequent modifications to those airplanes. It requires them to
perform design reviews and to develop design changes and maintenance
procedures if their designs do not meet the new fuel tank safety
standards. As explained in the preamble to the final rule published on
May 7, 2001, the FAA intended to adopt airworthiness directives to
mandate any changes found necessary to address unsafe conditions
identified as a result of these reviews.
In evaluating these design reviews, the FAA has established four
criteria intended to define the unsafe conditions associated with fuel
tank systems that require corrective actions. The percentage of
operating time during which fuel tanks are exposed to flammable
conditions is one of these criteria. The other three criteria address
the failure types under evaluation: Single failures, single failures in
combination with another latent condition(s), and in-service failure
experience. For all four criteria, the evaluations included
consideration of previous actions taken that may mitigate the need for
further action.
The FAA has determined that the actions identified in this proposed
AD are necessary to reduce the potential of ignition sources inside
fuel tanks, which, in combination with flammable fuel vapors, could
result in fuel tank explosions and consequent loss of the airplane.
The FAA has received data from the fuel tank inspection program
indicating that the existing bond path design provides insufficient
bond resistance margin between the fuel pump motor/impeller and
structure. In the event of a fuel pump electrical fault, this condition
might cause arcs at the existing fuel pump/tank interfaces and an
ignition of fuel vapor in the wing fuel tank, which could result in a
fuel tank explosion.
Related Service Information Under 1 CFR Part 51
The FAA reviewed Boeing Service Bulletin 747-28-2228, Revision 1,
dated September 27, 2001. This service information describes procedures
for a replacement of the bonding jumpers on the APU fuel pump; an
inspection of the six override/jettison fuel pumps and of the two
transfer/jettison fuel pumps to determine if the bonding jumper has a
one-piece braid or two-piece braid, and replacement of the existing
bonding jumper if the bonding jumper has a one-piece braid;
installation of a second bonding jumper; and replacement of the bonding
jumper on the electrical scavenge fuel pump.
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.
Other Relevant Rulemaking
Boeing Service Bulletin 747-28-2228, Revision 1, dated September
27, 2001, identifies ``Boeing Service Bulletin 747-28-2033'' as a
concurrent requirement for certain airplanes. Boeing Alert Service
Bulletin 747-28A2033, Revision 1, dated December 18, 2003, is the
appropriate source of service information for accomplishing the
installation required by AD 2005-01-07, Amendment 39-13931 (70 FR 1336,
January 7, 2005) (``AD 2005-01-07''). The compliance time for
accomplishing the installation required by AD 2005-01-07 has already
passed; therefore, it is not necessary to include Boeing Alert Service
Bulletin 747-28A2033 as a concurrent requirement in this proposed AD.
The FAA issued AD 2005-01-07 to
[[Page 60353]]
ensure adequate electrical bonding between the housing of each fuel
pump and airplane structure outside the fuel tanks. Inadequate
electrical bonding, in the event of a lightning strike or fuel pump
electrical fault, could cause electrical arcing and ignition of fuel
vapor in the wing fuel tank, which could result in a fuel tank
explosion.
FAA's Determination
The FAA is proposing this AD because the agency 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 accomplishing the actions specified
in the service information described previously.
Costs of Compliance
The FAA estimates that this proposed AD affects 74 airplanes of
U.S. registry. The FAA estimates the following costs to comply with
this proposed AD:
Estimated Costs
----------------------------------------------------------------------------------------------------------------
Cost on U.S.
Action Labor cost Parts cost Cost per product operators
----------------------------------------------------------------------------------------------------------------
Replacement, Installation, and Up to 15 work- Up to $2,000...... Up to $3,275...... Up to $242,350.
Inspection. hours x $85 per
hour = Up to
$1,275.
----------------------------------------------------------------------------------------------------------------
The FAA estimates the following costs to do any necessary
replacements that would be required based on the results of the
proposed inspection. The FAA has no way of determining the number of
aircraft that might need these replacements:
On-Condition Costs
----------------------------------------------------------------------------------------------------------------
Action Labor cost Parts cost Cost per product
----------------------------------------------------------------------------------------------------------------
Replacement.......................... Up to 6 work-hours x Up to $950............. Up to $1,460.
$85 per hour = Up to
$510.
----------------------------------------------------------------------------------------------------------------
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.
The FAA is 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
The FAA 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 this proposed
regulation:
(1) Is not a ``significant regulatory action'' under Executive
Order 12866,
(2) Will not affect intrastate aviation in Alaska, and
(3) 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-2019-0859; Product Identifier
2019-NM-114-AD.
(a) Comments Due Date
The FAA must receive comments by December 23, 2019.
(b) Affected ADs
None.
(c) Applicability
This AD applies to The Boeing Company Model 747-100, 747-100B,
747-100B SUD, 747-200B, 747-200C, 747-200F, 747-300, 747-400, 747-
400D, 747-400F, 747SR, and 747SP series airplanes, certificated in
any category, line numbers (L/Ns) 1 through 1229 inclusive.
(d) Subject
Air Transport Association (ATA) of America Code 28, Fuel.
(e) Unsafe Condition
This AD was prompted by fuel system reviews conducted by the
manufacturer indicating that the existing bond path design
[[Page 60354]]
provides insufficient bond resistance margin between the fuel pump
motor/impeller and structure. The FAA is issuing this AD to address
insufficient bond resistance margin between the fuel pump motor/
impeller and structure. In the event of a fuel pump electrical
fault, this condition might cause arcs at the existing fuel pump/
tank interfaces and an ignition of fuel vapor in the wing fuel tank,
which could result in a fuel tank explosion and consequent loss of
the airplane.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(g) Definitions
For the purposes of this AD, the definitions specified in
paragraphs (g)(1) through (4) of this AD apply.
(1) Group 1 airplanes: L/Ns 1 through 167 inclusive.
(2) Group 2 airplanes: L/Ns 168 through 971 inclusive.
(3) Group 3 airplanes: L/Ns 972 through 1161 inclusive.
(4) Group 4 airplanes: L/Ns 1162 through 1229 inclusive.
(h) Replacement, Installation, and Inspection
Within 60 months after the effective date of this AD, do the
applicable actions specified in paragraphs (h)(1) through (4) of
this AD, in accordance with the Accomplishment Instructions of
Boeing Service Bulletin 747-28-2228, Revision 1, dated September 27,
2001.
(1) For Groups 1, 2, and 3 airplanes: Do the actions specified
in paragraphs (h)(1)(i) and (ii) of this AD.
(i) Do a general visual inspection of the six override/jettison
fuel pumps to determine if the bonding jumper has a one-piece braid
or two-piece braid. If the bonding jumper has a one-piece braid,
within 60 months after the effective date of this AD, replace the
existing bonding jumper.
(ii) Install a second bonding jumper.
(2) For Groups 1, 2 and 3 airplanes with horizontal stabilizer
fuel tanks: Do the actions specified in paragraphs (h)(2)(i) and
(ii) of this AD.
(i) Do a general visual inspection of the two transfer/jettison
fuel pumps to determine if the bonding jumper has a one-piece braid
or a two-piece braid. If the bonding jumper has a one-piece braid,
within 60 months after the effective date of this AD, replace the
existing bonding jumper.
(ii) Install a second bonding jumper.
(3) For all airplanes: Replace the bonding jumpers on the
auxiliary power unit (APU) fuel pump.
(4) For Groups 1 and 2 airplanes: Replace the bonding jumper on
the electrical scavenge fuel pump.
(i) 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 (j)(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 Company 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.
(j) Related Information
(1) For more information about this AD, contact Jeffrey Rothman,
Aerospace Engineer, Propulsion Section, FAA, Seattle ACO Branch,
2200 South 216th St., Des Moines, WA 98198; phone and fax: 206-231-
3558; 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 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 October 29, 2019.
Dionne Palermo,
Acting Director, System Oversight Division, Aircraft Certification
Service.
[FR Doc. 2019-24329 Filed 11-7-19; 8:45 am]
BILLING CODE 4910-13-P
