[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
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Cost on U.S.
Action Labor cost Parts cost Cost per product operators
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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.
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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.
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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.
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]
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