Airworthiness Directives; The Boeing Company Airplanes, 59009-59013 [2021-23268]
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59009
Rules and Regulations
Federal Register
Vol. 86, No. 204
Tuesday, October 26, 2021
This section of the FEDERAL REGISTER
contains regulatory documents having general
applicability and legal effect, most of which
are keyed to and codified in the Code of
Federal Regulations, which is published under
50 titles pursuant to 44 U.S.C. 1510.
The Code of Federal Regulations is sold by
the Superintendent of Documents.
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2021–0099; Project
Identifier AD–2020–01272–T; Amendment
39–21757; AD 2021–20–19]
RIN 2120–AA64
Airworthiness Directives; The Boeing
Company Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule.
AGENCY:
The FAA is adopting a new
airworthiness directive (AD) for certain
The Boeing Company Model 767–200,
–300, –300F, and –400ER series
airplanes. This AD was prompted by
significant changes made to the
airworthiness limitations (AWLs)
related to fuel tank ignition prevention
and the nitrogen generation system.
This AD requires revising the existing
maintenance or inspection program, as
applicable, to incorporate the latest
revision of the AWLs. The FAA is
issuing this AD to address the unsafe
condition on these products.
DATES: This AD is effective November
30, 2021.
The Director of the Federal Register
approved the incorporation by reference
of a certain publication listed in this AD
as of November 30, 2021.
ADDRESSES: For service information
identified in this final rule, 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, Airworthiness Products Section,
Operational Safety Branch, 2200 South
216th St., Des Moines, WA. For
information on the availability of this
material at the FAA, call 206–231–3195.
SUMMARY:
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It is also available at https://
www.regulations.gov by searching for
and locating Docket No. FAA–2021–
0099.
Examining the AD Docket
You may examine the AD docket at
https://www.regulations.gov by
searching for and locating Docket No.
FAA–2021–0099; 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
final rule, any comments received, and
other information. The address for
Docket Operations is U.S. Department of
Transportation, Docket Operations, M–
30, West Building Ground Floor, Room
W12–140, 1200 New Jersey Avenue SE,
Washington, DC 20590.
FOR FURTHER INFORMATION CONTACT:
Douglas Mansell, Aerospace Engineer,
Propulsion Section, FAA, Seattle ACO
Branch, 2200 South 216th St., Des
Moines, WA 98198; phone and fax: 206–
231–3875; email: douglas.e.mansell@
faa.gov.
SUPPLEMENTARY INFORMATION:
Background
The FAA issued a notice of proposed
rulemaking (NPRM) to amend 14 CFR
part 39 by adding an AD that would
apply to certain The Boeing Company
Model 767–200, –300, –300F, and
–400ER series airplanes. The NPRM
published in the Federal Register on
February 26, 2021 (86 FR 11653). The
NPRM was prompted by significant
changes made to the airworthiness
limitations (AWLs) related to fuel tank
ignition prevention and the nitrogen
generation system. In the NPRM, the
FAA proposed to require revising the
existing maintenance or inspection
program, as applicable, to incorporate
the latest revision of the AWLs. The
FAA is issuing this AD to address the
potential for ignition sources inside fuel
tanks caused by latent failures,
alterations, repairs, or maintenance
actions, which, in combination with
flammable fuel vapors, could result in a
fuel tank explosion and consequent loss
of the airplane.
Discussion of Final Airworthiness
Directive
Comments
The FAA received comments from
The Air Line Pilots Association,
International (ALPA), and an
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individual, both of whom supported the
NPRM without change.
The FAA received additional
comments from five commenters,
including Aviation Partners Boeing
(APB), Boeing, Japan Airlines (JAL),
United Airlines (UAL), and United
Parcel Service (UPS). The following
presents the comments received on the
NPRM and the FAA’s response to each
comment.
Effect of Winglets on Accomplishment
of the Proposed Actions
APB stated that accomplishing
Supplemental Type Certificate (STC)
ST01920SE does not affect the actions
specified in the NPRM.
The FAA agrees with the commenter
that STC ST01920SE does not affect the
accomplishment of the manufacturer’s
service instructions. Therefore, the
installation of STC ST01920SE does not
affect the ability to accomplish the
actions required by this AD. The FAA
has not changed this AD in this regard.
Request To Remove Certain
‘‘Unqualified’’ Items
Boeing requested that paragraphs
(h)(1) and (2) of the proposed AD be
deleted to remove unqualified wire
types and wire sleeving from the list of
acceptable wire types and sleeving.
Boeing declared that it has qualified and
certified wire types BMS 13–48, BMS
13–58, and BMS 13–60, as well as
Teflon wire sleeving TFE–2X, but has
not certified the additional types for
Boeing airplanes.
The FAA does not agree to remove the
paragraphs as requested. Since the
issuance of AD 2008–11–01 R1,
Amendment 39–16145 (74 FR 68515,
December 28, 2009) (AD 2008–11–01
R1), which will be terminated by this
AD, the FAA received numerous
requests for approval of alternative
methods of compliance (AMOCs) from
operators and STC holders (or
applicants) to allow the installation of
the alternative wire types and sleeving
identified in paragraphs (h)(1) and (2) of
this AD. The FAA evaluated key
attributes of those alternative wire types
and sleeving for each installation, and
issued numerous AMOC approvals
based on the determination that
installing those wire types and sleeving
would provide an acceptable level of
safety. Although paragraph (h) of this
AD provides certain allowances, it does
not provide approval of alternative wire
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types and sleeving that are installed as
part of an aircraft design change. Each
applicant for any design change is still
responsible to show that the installation
of alternative wire types and sleeving
identified in paragraphs (h)(1) and (2) of
this AD complies with all applicable
regulatory requirements. This
responsibility includes, but is not
limited to, substantiation of compliance
with flammability requirements, and
substantiation that shows that sleeve
installation, including the selection of
sleeve thickness, is adequate to protect
wires from chafing for the life of the
installation. If such an installation is
found to be compliant with all
applicable regulatory requirements,
revision of AWL No. 28–AWL–09 in
accordance with paragraph (h) of this
AD would allow the installation of the
alternative wire types and sleeving. The
FAA has not changed this AD with
regard to this request.
Request To Exempt Certain Airplanes
From Initial Compliance Times
UAL recommended that airplanes in
long-term storage be exempted from the
applicable initial compliance times, and
that the ALI tasks be accomplished at
the applicable initial compliance times
after return to service. UAL stated that
many of the affected airplanes are now
in long-term storage.
The FAA does not agree to extend the
compliance time to begin after return to
service for airplanes in long-term
storage. In developing an appropriate
compliance time for the tasks required
by this AD, the FAA considered relevant
safety issues as well as Boeing’s
recommendations. The FAA concluded
that the inspections must be completed
as stated in revised paragraphs (g)(1)
through (14) of this AD, although the
FAA may consider requests for approval
of AMOCs from operators with special
circumstances. This AD has not been
changed with regard to this request.
Request for Clarification of Initial
Compliance Times
JAL requested clarification about
whether the initial compliance time for
airplanes with no initial inspections
performed or with Boeing Service
Bulletin 767–47–0001 incorporated is
the ALI’s threshold from airplane
delivery or the accomplishment date of
the service bulletin. JAL asserted that in
similar FAA ADs or proposed ADs, the
initial compliance time for airplanes
with no inspections performed is the
ALI’s threshold from airplane delivery.
The FAA agrees with JAL’s assertions,
and has determined that neverinspected airplanes should be allowed
the full compliance time (the applicable
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AWL interval) from airplane delivery.
Furthermore, airplanes for which the
referenced AWL was not previously
included in the operator’s maintenance/
inspection program should be allowed a
grace period if the AWL interval has
passed.
For the foregoing reasons, the FAA
has revised the compliance times for the
initial tasks in paragraphs (g)(1) through
(14) of this AD. While the revised
paragraphs may appear significantly
different from those in the proposed AD,
the compliance times are the same as
proposed for most operators—except for
the extension of certain compliance
times that will provide relief for some
operators. The FAA’s safety assessment
indicates that these changes will
provide an acceptable level of safety.
The proposed AD has been changed in
the following ways:
• The compliance times for each
AWL are provided for two groups of
airplanes, based on whether their
maintenance program had previously
included the specific AWL. The AWLs
that are included in an operator’s
maintenance program depend on several
factors, including the certification basis
for the airplane and applicable
regulations including airworthiness
directives in effect when the airplane is
produced and subsequent to airplane
delivery. Therefore, some AWLs
identified in paragraph (g) of this AD
may not have previously been included
in the existing maintenance program.
• For an AWL that was previously
incorporated, the airplane, whether
previously inspected or not, is provided
the full compliance time. Although the
proposed AD would have required
inspecting never-inspected airplanes
within the shorter grace period, the FAA
had intended to provide the full interval
specified in the AWL, starting from
airplane delivery or from the last
inspection.
• The FAA has revised the grace
period from 30 days to 60 days in
paragraphs (g)(2), (4), (6), (7), (9), (10),
(11), and (12) of this AD. With this
change, compliance for those specific
tasks will not be required earlier than
the compliance time to revise the
maintenance program.
Request To Update Applicability
UPS requested an update to paragraph
(c), ‘‘Applicability,’’ of the proposed AD
to specify airplanes ‘‘as identified in’’
Boeing 767–200/300/300F/400ER
Special Compliance Items/
Airworthiness Limitations, D622T001–
9–04, dated January 2020. UPS stated
that the update is needed to clarify that
each task within Boeing 767–200/300/
300F/400ER Special Compliance Items/
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Airworthiness Limitations, D622T001–
9–04, dated January 2020, is required
only for the airplanes for which it is
identified as applicable, and not for all
airplanes having L/N 1 through 1200
inclusive regardless of the task
applicability.
The FAA disagrees with the request.
Each task in Boeing 767–200/300/300F/
400ER Special Compliance Items/
Airworthiness Limitations, D622T001–
9–04, dated January 2020, is required
only for specific airplanes, but
paragraph (c), ‘‘Applicability,’’ of this
AD must include every airplane that is
subject to any requirement in the AD.
This AD has not been changed with
regard to this request.
Conclusion
The FAA reviewed the relevant data,
considered any comments received, and
determined that air safety requires
adopting this AD as proposed. Except
for minor editorial changes, and any
other changes described previously, this
AD is adopted as proposed in the
NPRM. None of the changes will
increase the economic burden on any
operator.
Related Service Information Under 1
CFR Part 51
The FAA reviewed Boeing 767–200/
300/300F/400ER Special Compliance
Items/Airworthiness Limitations,
D622T001–9–04, dated January 2020.
This service information describes
AWLs that include airworthiness
limitation instructions (ALIs) and
critical design configuration control
limitations (CDCCLs) tasks related to
fuel tank ignition prevention and the
nitrogen generation system. This service
information is reasonably available
because the interested parties have
access to it through their normal course
of business or by the means identified
in the ADDRESSES section.
Costs of Compliance
The FAA estimates that this AD
affects 500 airplanes of U.S. registry.
The FAA estimates the following costs
to comply with this AD:
The FAA has determined that revising
the existing maintenance or inspection
program takes an average of 90 workhours per operator, although the agency
recognizes that this number may vary
from operator to operator. Since
operators incorporate maintenance or
inspection program changes for their
affected fleet(s), the FAA has
determined that a per-operator estimate
is more accurate than a per-airplane
estimate. Therefore, the FAA estimates
the average total cost per operator to be
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$7,650 (90 work-hours × $85 per workhour).
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.
Regulatory Findings
This AD will not have federalism
implications under Executive Order
13132. This AD will not have a
substantial direct effect on the States, on
the relationship between the national
government and the States, or on the
distribution of power and
responsibilities among the various
levels of government.
For the reasons discussed above, I
certify that this AD:
(1) Is not a ‘‘significant regulatory
action’’ under Executive Order 12866,
(2) 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 Amendment
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.
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[Amended]
2. The FAA amends § 39.13 by adding
the following new airworthiness
directive:
2021–20–19 The Boeing Company:
Amendment 39–21757; Docket No.
FAA–2021–0099; Project Identifier AD–
2020–01272–T.
(a) Effective Date
This airworthiness directive (AD) is
effective November 30, 2021.
(b) Affected ADs
This AD affects the ADs specified in
paragraphs (b)(1) through (7) of this AD.
(1) AD 2008–11–01 R1, Amendment 39–
16145 (74 FR 68515, December 28, 2009) (AD
2008–11–01 R1).
(2) AD 2010–06–10, Amendment 39–16234
(75 FR 15322, March 29, 2010) (AD 2010–06–
10).
(3) AD 2011–25–05, Amendment 39–16881
(77 FR 2442, January 18, 2012) (AD 2011–25–
05).
(4) AD 2013–25–02, Amendment 39–17698
(79 FR 24541, May 1, 2014) (AD 2013–25–
02).
(5) AD 2014–08–09, Amendment 39–17833
(79 FR 24546, May 1, 2014) (AD 2014–08–
09).
(6) AD 2014–20–02, Amendment 39–17975
(79 FR 59102, October 1, 2014) (AD 2014–20–
02).
(7) AD 2018–20–13, Amendment 39–19447
(83 FR 52305, October 17, 2018) (AD 2018–
20–13).
(c) Applicability
This AD applies to The Boeing Company
Model 767–200, –300, –300F, and –400ER
series airplanes, certificated in any category,
having line numbers (L/N) 1 through 1200
inclusive.
(d) Subject
Air Transport Association (ATA) of
America Code 28, Fuel.
(e) Unsafe Condition
This AD was prompted by significant
changes made to the airworthiness
limitations (AWLs) related to fuel tank
ignition prevention and the nitrogen
generation system. The FAA is issuing this
AD to address the potential for ignition
sources inside fuel tanks caused by latent
failures, alterations, repairs, or maintenance
actions, which, in combination with
flammable fuel vapors, 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.
Accordingly, under the authority
delegated to me by the Administrator,
the FAA amends 14 CFR part 39 as
follows:
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§ 39.13
■
(g) Maintenance or Inspection Program
Revision
Within 60 days after the effective date of
this AD, revise the existing maintenance or
inspection program, as applicable, to
incorporate the applicable information in
Section A, including Subsections A.1, A.2,
A.3, A.4, and A.5, of Boeing 767–200/300/
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59011
300F/400ER Special Compliance Items/
Airworthiness Limitations, D622T001–9–04,
dated January 2020; except as provided by
paragraph (h) of this AD. The initial
compliance times for the airworthiness
limitation instructions (ALI) tasks are within
the applicable compliance times specified in
paragraphs (g)(1) through (14) of this AD:
(1) For airplanes identified in the
applicability for AWL No. 28–AWL–01,
‘‘External Wires Over Auxiliary (Center) Fuel
Tank’’: At the applicable time specified in
paragraph (g)(1)(i) or (ii) of this AD.
(i) For airplanes that did not have any
version of AWL No. 28–AWL–01 in their
maintenance or inspection program before
the effective date of this AD: Within 144
months since issuance of the original
airworthiness certificate or original export
certificate of airworthiness, or within 12
months after the effective date of this AD,
whichever occurs later.
(ii) For airplanes not identified in
paragraph (g)(1)(i) of this AD: Within 144
months since issuance of the original
airworthiness certificate or original export
certificate of airworthiness, or within 144
months after the most recent inspection, if
any, was performed as specified in AWL No.
28–AWL–01; whichever occurs later.
(2) For airplanes identified in the
applicability for AWL No. 28–AWL–05,
‘‘Lightning Protection—Hydraulic Line Fuel
Tank Penetration Bonding Path’’: At the
applicable time specified in paragraph
(g)(2)(i) or (ii) of this AD.
(i) For airplanes that did not have any
version of AWL No. 28–AWL–05 in their
maintenance or inspection program before
the effective date of this AD: At the later of
the times specified in paragraphs (g)(2)(i)(A)
and (B) of this AD.
(A) Within 25,000 flight hours or 72
months, whichever occurs first since
issuance of the original airworthiness
certificate or original export certificate of
airworthiness.
(B) Within 60 days after the effective date
of this AD.
(ii) For airplanes not identified in
paragraph (g)(2)(i) of this AD: At the later of
the times specified in paragraphs (g)(2)(ii)(A)
and (B) of this AD.
(A) Within 25,000 flight hours or 72
months, whichever occurs first since
issuance of the original airworthiness
certificate or original export certificate of
airworthiness.
(B) Within 25,000 flight hours or 72
months, whichever occurs first after the most
recent inspection, if any, was performed as
specified in AWL No. 28–AWL–05.
(3) For airplanes identified in the
applicability for AWL No. 28–AWL–18,
‘‘Fuel Quantity Indicating System (FQIS)—
Out of Tank Wiring Lightning Shield to
Ground Termination’’: At the applicable time
specified in paragraph (g)(3)(i) or (ii) of this
AD.
(i) For airplanes that did not have any
version of AWL No. 28–AWL–18 in their
maintenance or inspection program before
the effective date of this AD: Within 144
months since issuance of the original
airworthiness certificate or original export
certificate of airworthiness, or within 12
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months after the effective date of this AD,
whichever occurs later.
(ii) For airplanes not identified in
paragraph (g)(3)(i) of this AD: Within 144
months since issuance of the original
airworthiness certificate or original export
certificate of airworthiness, or within 144
months after the most recent inspection, if
any, was performed as specified in AWL No.
28–AWL–18; whichever occurs later.
(4) For airplanes identified in the
applicability for AWL No. 28–AWL–20,
‘‘Auxiliary (Center) Tank Override Fuel
Pumps Auto Shutoff Circuit’’: At the
applicable time specified in paragraph
(g)(4)(i) or (ii) of this AD.
(i) For airplanes that did not have any
version of AWL No. 28–AWL–20 in their
maintenance or inspection program before
the effective date of this AD: Within 12
months since issuance of the original
airworthiness certificate or original export
certificate of airworthiness, or within 60 days
after the effective date of this AD, whichever
occurs later.
(ii) For airplanes not identified in
paragraph (g)(4)(i) of this AD: At the latest of
the times specified in paragraphs (g)(4)(ii)(A)
through (C) of this AD.
(A) Within 12 months since issuance of the
original airworthiness certificate or original
export certificate of airworthiness.
(B) Within 12 months after the most recent
inspection, if any, was performed as
specified in AWL No. 28–AWL–20.
(C) Within 12 months after
accomplishment of the actions specified in
Boeing Service Bulletin 767–28A0083 or
Boeing Service Bulletin 767–28A0084, as
applicable.
(5) For airplanes identified in the
applicability for AWL No. 28–AWL–21, ‘‘AC
and DC Fuel Pump Fault Current Bonding
Jumper Installation’’: At the applicable time
specified in paragraph (g)(5)(i) or (ii) of this
AD.
(i) For airplanes that did not have any
version of AWL No. 28–AWL–21 in their
maintenance or inspection program before
the effective date of this AD: Within 72
months since issuance of the original
airworthiness certificate or original export
certificate of airworthiness, or within 6
months after the effective date of this AD,
whichever occurs later.
(ii) For airplanes not identified in
paragraph (g)(5)(i) of this AD: Within 72
months since issuance of the original
airworthiness certificate or original export
certificate of airworthiness, or within 72
months after the most recent inspection, if
any, was performed as specified in AWL No.
28–AWL–21; whichever occurs later.
(6) For airplanes identified in the
applicability for AWL No. 28–AWL–27,
‘‘Over-Current and Arcing Protection
Electrical Design Features Operation—AC
Fuel Pump Ground Fault Interrupter (GFI)’’:
At the applicable time specified in paragraph
(g)(6)(i) or (ii) of this AD.
(i) For airplanes that did not have any
version of AWL No. 28–AWL–27 in their
maintenance or inspection program before
the effective date of this AD: Within 12
months since issuance of the original
airworthiness certificate or original export
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certificate of airworthiness, or within 60 days
after the effective date of this AD, whichever
occurs later.
(ii) For airplanes not identified in
paragraph (g)(6)(i) of this AD: At the latest of
the times specified in paragraphs (g)(6)(ii)(A)
through (C) of this AD.
(A) Within 12 months since issuance of the
original airworthiness certificate or original
export certificate of airworthiness.
(B) Within 12 months after the most recent
inspection, if any, was performed as
specified in AWL No. 28–AWL–27.
(C) Within 12 months after
accomplishment of the actions specified in
Boeing Service Bulletin 767–28A0085.
(7) For airplanes identified in the
applicability for AWL No. 28–AWL–28,
‘‘Auxiliary (Center) Tank Override/Jettison
Fuel Pump Failed On Protection System’’: At
the applicable time specified in paragraph
(g)(7)(i) or (ii) of this AD.
(i) For airplanes that did not have any
version of AWL No. 28–AWL–28 in their
maintenance or inspection program before
the effective date of this AD: Within 12
months since issuance of the original
airworthiness certificate or original export
certificate of airworthiness, or within 60 days
after the effective date of this AD, whichever
occurs later.
(ii) For airplanes not identified in
paragraph (g)(7)(i) of this AD: At the latest of
the times specified in paragraphs (g)(7)(ii)(A)
through (C) of this AD.
(A) Within 12 months since issuance of the
original airworthiness certificate or original
export certificate of airworthiness.
(B) Within 12 months after the most recent
inspection, if any, was performed as
specified in AWL No. 28–AWL–28.
(C) Within 12 months after
accomplishment of the actions specified in
Boeing Service Bulletin 767–28A0085.
(8) For airplanes identified in the
applicability for AWL No. 28–AWL–35,
‘‘Cushion Clamps and Teflon Sleeving
Installed on Out-of-Tank Wire Bundles
Installed on Brackets that are Mounted
Directly on the Fuel Tanks’’: At the
applicable time specified in paragraph
(g)(8)(i) or (ii) of this AD.
(i) For airplanes that did not have any
version of AWL No. 28–AWL–35 in their
maintenance or inspection program before
the effective date of this AD: Within 144
months since issuance of the original
airworthiness certificate or original export
certificate of airworthiness, or within 12
months after the effective date of this AD,
whichever occurs later.
(ii) For airplanes not identified in
paragraph (g)(8)(i) of this AD: At the latest of
the times specified in paragraphs (g)(8)(ii)(A)
through (C) of this AD.
(A) Within 144 months since issuance of
the original airworthiness certificate or
original export certificate of airworthiness.
(B) Within 144 months after the most
recent inspection, if any, was performed as
specified in AWL No. 28–AWL–35.
(C) Within 144 months after
accomplishment of the actions specified in
Boeing Service Bulletin 767–57A0102.
(9) For airplanes identified in the
applicability for AWL No. 28–AWL–37,
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‘‘FQIS BITE Test (Auxiliary (Center) Tank
Circuit Test)’’: At the applicable time
specified in paragraph (g)(9)(i) or (ii) of this
AD.
(i) For airplanes that did not have any
version of AWL No. 28–AWL–37 in their
maintenance or inspection program before
the effective date of this AD: Within 750
flight hours since issuance of the original
airworthiness certificate or original export
certificate of airworthiness, or within 60 days
after the effective date of this AD, whichever
occurs later.
(ii) For airplanes not identified in
paragraph (g)(9)(i) of this AD: Within 750
flight hours since issuance of the original
airworthiness certificate or original export
certificate of airworthiness, or within 750
flight hours after the most recent inspection,
if any, was performed as specified in AWL
No. 28–AWL–37; whichever occurs later.
(10) For airplanes identified in the
applicability for AWL No. 28–AWL–38,
‘‘Fuel Level Sensing System (FLSS) Dry
Capacitance Test’’: At the applicable time
specified in paragraph (g)(10)(i) or (ii) of this
AD.
(i) For airplanes that did not have any
version of AWL No. 28–AWL–38 in their
maintenance or inspection program before
the effective date of this AD: Within 750
flight hours since issuance of the original
airworthiness certificate or original export
certificate of airworthiness, or within 60 days
after the effective date of this AD, whichever
occurs later.
(ii) For airplanes not identified in
paragraph (g)(10)(i) of this AD: Within 750
flight hours since issuance of the original
airworthiness certificate or original export
certificate of airworthiness, or within 750
flight hours after the most recent inspection,
if any, was performed as specified in AWL
No. 28–AWL–38; whichever occurs later.
(11) For airplanes identified in the
applicability for AWL No. 28–AWL–101,
‘‘Engine Fuel Suction Feed Operational
Test’’: At the applicable time specified in
paragraph (g)(11)(i) or (ii) of this AD.
(i) For airplanes that did not have any
version of AWL No. 28–AWL–101 in their
maintenance or inspection program before
the effective date of this AD: At the later of
the times specified in paragraphs (g)(11)(i)(A)
and (B) of this AD.
(A) Within 7,500 flight hours or 36 months,
whichever occurs first since issuance of the
original airworthiness certificate or original
export certificate of airworthiness.
(B) Within 60 days after the effective date
of this AD.
(ii) For airplanes not identified in
paragraph (g)(11)(i) of this AD: At the later
of the times specified in paragraphs
(g)(11)(ii)(A) and (B) of this AD.
(A) Within 7,500 flight hours or 36 months,
whichever occurs first since issuance of the
original airworthiness certificate or original
export certificate of airworthiness.
(B) Within 7,500 flight hours or 36 months,
whichever occurs first after the most recent
inspection, if any, was performed as
specified in AWL No. 28–AWL–101.
(12) For airplanes identified in the
applicability for AWL No. 28–AWL–102,
‘‘Fuel Quantity Indicating System (FQIS)—
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Low Fuel and Fuel Config Indication Test’’:
At the applicable time specified in paragraph
(g)(12)(i) or (ii) of this AD.
(i) For airplanes that did not have any
version of AWL No. 28–AWL–102 in their
maintenance or inspection program before
the effective date of this AD: Within 750
flight hours since issuance of the original
airworthiness certificate or original export
certificate of airworthiness; or within 60 days
after the effective date of this AD, whichever
occurs later.
(ii) For airplanes not identified in
paragraph (g)(12)(i) of this AD: At the latest
of the times specified in paragraphs
(g)(12)(ii)(A) through (C) of this AD.
(A) Within 750 flight hours since issuance
of the original airworthiness certificate or
original export certificate of airworthiness.
(B) Within 750 flight hours after the most
recent inspection, if any, was performed as
specified in AWL No. 28–AWL–102.
(C) Within 750 flight hours after
accomplishment of the actions specified in
Boeing Service Bulletin 767–31–0295 or
Boeing Service Bulletin 767–31–0302, as
applicable.
(13) For airplanes identified in the
applicability for AWL No. 47–AWL–04,
‘‘Nitrogen Generation System (NGS)—
Nitrogen-Enriched Air (NEA) Distribution
Ducting’’: At the applicable time specified in
paragraph (g)(13)(i) or (ii) of this AD.
(i) For airplanes that did not have any
version of AWL No. 47–AWL–04 in their
maintenance or inspection program before
the effective date of this AD: Within the
applicable interval specified in AWL No. 47–
AWL–04 since issuance of the original
airworthiness certificate or original export
certificate of airworthiness, or within 4
months after the effective date of this AD,
whichever occurs later.
(ii) For airplanes not identified in
paragraph (g)(13)(i) of this AD: Within the
applicable interval specified in AWL No. 47–
AWL–04 since issuance of the original
airworthiness certificate or original export
certificate of airworthiness, or within that
applicable interval since the most recent
inspection, if any, was performed as
specified in AWL No. 47–AWL–04;
whichever occurs later.
(14) For airplanes identified in the
applicability for AWL No. 47–AWL–05,
‘‘Nitrogen Generation System (NGS)—Cross
Vent Check Valve’’: At the applicable time
specified in paragraph (g)(14)(i) or (ii) of this
AD.
(i) For airplanes that did not have any
version of AWL No. 47–AWL–05 in their
maintenance or inspection program before
the effective date of this AD: Within the
applicable interval specified in AWL No. 47–
AWL–05 since issuance of the original
airworthiness certificate or original export
certificate of airworthiness, or within 4
months after the effective date of this AD,
whichever occurs later.
(ii) For airplanes not identified in
paragraph (g)(14)(i) of this AD: Within the
applicable interval specified in AWL No. 47–
AWL–05 since issuance of the original
airworthiness certificate or original export
certificate of airworthiness, or within that
applicable interval since the most recent
VerDate Sep<11>2014
15:52 Oct 25, 2021
Jkt 256001
inspection, if any, was performed as
specified in AWL No. 47–AWL–05;
whichever occurs later.
(h) Additional Acceptable Wire Types and
Sleeving
As an option, during accomplishment of
the actions required by paragraph (g) of this
AD, the changes specified in paragraphs
(h)(1) and (2) of this AD are acceptable.
(1) Where AWL No. 28–AWL–09 identifies
wire types BMS 13–48, BMS 13–58, and BMS
13–60, the following acceptable wire types
and cables can be added to AWL No. 28–
AWL–09: MIL–W–22759/16, SAE AS22759/
16 (formerly M22759/16), MIL–W–22759/32,
SAE AS22759/32 (formerly M22759/32),
MIL–W–22759/34, SAE AS22759/34
(formerly M22759/34), MIL–W–22759/41,
SAE AS22759/41 (formerly M22759/41),
MIL–W–22759/86, SAE AS22759/86
(formerly M22759/86), MIL–W–22759/87,
SAE AS22759/87 (formerly M22759/87),
MIL–W–22759/92, and SAE AS22759/92
(formerly M22759/92); and MIL–C–27500
and NEMA WC 27500 cables that are
constructed from these military or SAE
specification wire types, as applicable.
(2) Where AWL No. 28–AWL–09 identifies
TFE–2X Standard wall for wire sleeving, the
following sleeving materials are acceptable:
Roundit 2000NX and Varglas Type HO, HP,
or HM, Grade A.
(i) No Alternative Actions, Intervals, or
Critical Design Configuration Control
Limitations (CDCCLs)
After the existing maintenance or
inspection program has been revised as
required by paragraph (g) of this AD, no
alternative actions (e.g., inspections),
intervals, or CDCCLs may be used unless the
actions, intervals, and CDCCLs are approved
as an alternative method of compliance
(AMOC) in accordance with the procedures
specified in paragraph (k) of this AD.
(j) Terminating Action for Certain AD
Requirements
Accomplishment of the revision required
by paragraph (g) of this AD terminates the
requirements specified in paragraphs (j)(1)
through (7) of this AD for that airplane:
(1) The revision required by paragraphs (g)
and (h) of AD 2008–11–01 R1.
(2) The revision required by paragraph (h)
of AD 2010–06–10.
(3) The revision required by paragraph (k)
of AD 2011–25–05.
(4) The revision required by paragraph (n)
of AD 2013–25–02.
(5) The revision required by paragraph (g)
of AD 2014–08–09.
(6) The revision required by paragraph (h)
of AD 2014–20–02.
(7) The revision required by paragraphs
(i)(3)(i) and (ii) of AD 2018–20–13.
(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 responsible Flight
Standards Office, as appropriate. If sending
PO 00000
Frm 00005
Fmt 4700
Sfmt 4700
59013
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 responsible Flight Standards 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.
(l) Related Information
For more information about this AD,
contact Douglas Mansell, Aerospace
Engineer, Propulsion Section, FAA, Seattle
ACO Branch, 2200 South 216th St., Des
Moines, WA 98198; phone and fax: 206–231–
3875; email: douglas.e.mansell@faa.gov.
(m) Material Incorporated by Reference
(1) The Director of the Federal Register
approved the incorporation by reference
(IBR) of the service information listed in this
paragraph under 5 U.S.C. 552(a) and 1 CFR
part 51.
(2) You must use this service information
as applicable to do the actions required by
this AD, unless the AD specifies otherwise.
(i) Boeing 767–200/300/300F/400ER
Special Compliance Items/Airworthiness
Limitations, D622T001–9–04, dated January
2020.
(ii) [Reserved]
(3) 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.
(4) You may view this service information
at the FAA, Airworthiness Products Section,
Operational Safety Branch, 2200 South 216th
St., Des Moines, WA. For information on the
availability of this material at the FAA, call
206–231–3195.
(5) You may view this service information
that is incorporated by reference at the
National Archives and Records
Administration (NARA). For information on
the availability of this material at NARA,
email fr.inspection@nara.gov, or go to:
https://www.archives.gov/federal-register/cfr/
ibr-locations.html.
Issued on September 23, 2021.
Lance T. Gant,
Director, Compliance & Airworthiness
Division, Aircraft Certification Service.
[FR Doc. 2021–23268 Filed 10–25–21; 8:45 am]
BILLING CODE 4910–13–P
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]]>Agencies
[Federal Register Volume 86, Number 204 (Tuesday, October 26, 2021)]
[Rules and Regulations]
[Pages 59009-59013]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2021-23268]
========================================================================
Rules and Regulations
Federal Register
________________________________________________________________________
This section of the FEDERAL REGISTER contains regulatory documents
having general applicability and legal effect, most of which are keyed
to and codified in the Code of Federal Regulations, which is published
under 50 titles pursuant to 44 U.S.C. 1510.
The Code of Federal Regulations is sold by the Superintendent of Documents.
========================================================================
Federal Register / Vol. 86, No. 204 / Tuesday, October 26, 2021 /
Rules and Regulations
[[Page 59009]]
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2021-0099; Project Identifier AD-2020-01272-T;
Amendment 39-21757; AD 2021-20-19]
RIN 2120-AA64
Airworthiness Directives; The Boeing Company Airplanes
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Final rule.
-----------------------------------------------------------------------
SUMMARY: The FAA is adopting a new airworthiness directive (AD) for
certain The Boeing Company Model 767-200, -300, -300F, and -400ER
series airplanes. This AD was prompted by significant changes made to
the airworthiness limitations (AWLs) related to fuel tank ignition
prevention and the nitrogen generation system. This AD requires
revising the existing maintenance or inspection program, as applicable,
to incorporate the latest revision of the AWLs. The FAA is issuing this
AD to address the unsafe condition on these products.
DATES: This AD is effective November 30, 2021.
The Director of the Federal Register approved the incorporation by
reference of a certain publication listed in this AD as of November 30,
2021.
ADDRESSES: For service information identified in this final rule,
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, Airworthiness Products Section, Operational Safety 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 at
https://www.regulations.gov by searching for and locating Docket No.
FAA-2021-0099.
Examining the AD Docket
You may examine the AD docket at https://www.regulations.gov by
searching for and locating Docket No. FAA-2021-0099; 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 final rule, any
comments received, and other information. The address for Docket
Operations is U.S. Department of Transportation, Docket Operations, M-
30, West Building Ground Floor, Room W12-140, 1200 New Jersey Avenue
SE, Washington, DC 20590.
FOR FURTHER INFORMATION CONTACT: Douglas Mansell, Aerospace Engineer,
Propulsion Section, FAA, Seattle ACO Branch, 2200 South 216th St., Des
Moines, WA 98198; phone and fax: 206-231-3875; email:
[email protected].
SUPPLEMENTARY INFORMATION:
Background
The FAA issued a notice of proposed rulemaking (NPRM) to amend 14
CFR part 39 by adding an AD that would apply to certain The Boeing
Company Model 767-200, -300, -300F, and -400ER series airplanes. The
NPRM published in the Federal Register on February 26, 2021 (86 FR
11653). The NPRM was prompted by significant changes made to the
airworthiness limitations (AWLs) related to fuel tank ignition
prevention and the nitrogen generation system. In the NPRM, the FAA
proposed to require revising the existing maintenance or inspection
program, as applicable, to incorporate the latest revision of the AWLs.
The FAA is issuing this AD to address the potential for ignition
sources inside fuel tanks caused by latent failures, alterations,
repairs, or maintenance actions, which, in combination with flammable
fuel vapors, could result in a fuel tank explosion and consequent loss
of the airplane.
Discussion of Final Airworthiness Directive
Comments
The FAA received comments from The Air Line Pilots Association,
International (ALPA), and an individual, both of whom supported the
NPRM without change.
The FAA received additional comments from five commenters,
including Aviation Partners Boeing (APB), Boeing, Japan Airlines (JAL),
United Airlines (UAL), and United Parcel Service (UPS). The following
presents the comments received on the NPRM and the FAA's response to
each comment.
Effect of Winglets on Accomplishment of the Proposed Actions
APB stated that accomplishing Supplemental Type Certificate (STC)
ST01920SE does not affect the actions specified in the NPRM.
The FAA agrees with the commenter that STC ST01920SE does not
affect the accomplishment of the manufacturer's service instructions.
Therefore, the installation of STC ST01920SE does not affect the
ability to accomplish the actions required by this AD. The FAA has not
changed this AD in this regard.
Request To Remove Certain ``Unqualified'' Items
Boeing requested that paragraphs (h)(1) and (2) of the proposed AD
be deleted to remove unqualified wire types and wire sleeving from the
list of acceptable wire types and sleeving. Boeing declared that it has
qualified and certified wire types BMS 13-48, BMS 13-58, and BMS 13-60,
as well as Teflon wire sleeving TFE-2X, but has not certified the
additional types for Boeing airplanes.
The FAA does not agree to remove the paragraphs as requested. Since
the issuance of AD 2008-11-01 R1, Amendment 39-16145 (74 FR 68515,
December 28, 2009) (AD 2008-11-01 R1), which will be terminated by this
AD, the FAA received numerous requests for approval of alternative
methods of compliance (AMOCs) from operators and STC holders (or
applicants) to allow the installation of the alternative wire types and
sleeving identified in paragraphs (h)(1) and (2) of this AD. The FAA
evaluated key attributes of those alternative wire types and sleeving
for each installation, and issued numerous AMOC approvals based on the
determination that installing those wire types and sleeving would
provide an acceptable level of safety. Although paragraph (h) of this
AD provides certain allowances, it does not provide approval of
alternative wire
[[Page 59010]]
types and sleeving that are installed as part of an aircraft design
change. Each applicant for any design change is still responsible to
show that the installation of alternative wire types and sleeving
identified in paragraphs (h)(1) and (2) of this AD complies with all
applicable regulatory requirements. This responsibility includes, but
is not limited to, substantiation of compliance with flammability
requirements, and substantiation that shows that sleeve installation,
including the selection of sleeve thickness, is adequate to protect
wires from chafing for the life of the installation. If such an
installation is found to be compliant with all applicable regulatory
requirements, revision of AWL No. 28-AWL-09 in accordance with
paragraph (h) of this AD would allow the installation of the
alternative wire types and sleeving. The FAA has not changed this AD
with regard to this request.
Request To Exempt Certain Airplanes From Initial Compliance Times
UAL recommended that airplanes in long-term storage be exempted
from the applicable initial compliance times, and that the ALI tasks be
accomplished at the applicable initial compliance times after return to
service. UAL stated that many of the affected airplanes are now in
long-term storage.
The FAA does not agree to extend the compliance time to begin after
return to service for airplanes in long-term storage. In developing an
appropriate compliance time for the tasks required by this AD, the FAA
considered relevant safety issues as well as Boeing's recommendations.
The FAA concluded that the inspections must be completed as stated in
revised paragraphs (g)(1) through (14) of this AD, although the FAA may
consider requests for approval of AMOCs from operators with special
circumstances. This AD has not been changed with regard to this
request.
Request for Clarification of Initial Compliance Times
JAL requested clarification about whether the initial compliance
time for airplanes with no initial inspections performed or with Boeing
Service Bulletin 767-47-0001 incorporated is the ALI's threshold from
airplane delivery or the accomplishment date of the service bulletin.
JAL asserted that in similar FAA ADs or proposed ADs, the initial
compliance time for airplanes with no inspections performed is the
ALI's threshold from airplane delivery.
The FAA agrees with JAL's assertions, and has determined that
never-inspected airplanes should be allowed the full compliance time
(the applicable AWL interval) from airplane delivery. Furthermore,
airplanes for which the referenced AWL was not previously included in
the operator's maintenance/inspection program should be allowed a grace
period if the AWL interval has passed.
For the foregoing reasons, the FAA has revised the compliance times
for the initial tasks in paragraphs (g)(1) through (14) of this AD.
While the revised paragraphs may appear significantly different from
those in the proposed AD, the compliance times are the same as proposed
for most operators--except for the extension of certain compliance
times that will provide relief for some operators. The FAA's safety
assessment indicates that these changes will provide an acceptable
level of safety. The proposed AD has been changed in the following
ways:
The compliance times for each AWL are provided for two
groups of airplanes, based on whether their maintenance program had
previously included the specific AWL. The AWLs that are included in an
operator's maintenance program depend on several factors, including the
certification basis for the airplane and applicable regulations
including airworthiness directives in effect when the airplane is
produced and subsequent to airplane delivery. Therefore, some AWLs
identified in paragraph (g) of this AD may not have previously been
included in the existing maintenance program.
For an AWL that was previously incorporated, the airplane,
whether previously inspected or not, is provided the full compliance
time. Although the proposed AD would have required inspecting never-
inspected airplanes within the shorter grace period, the FAA had
intended to provide the full interval specified in the AWL, starting
from airplane delivery or from the last inspection.
The FAA has revised the grace period from 30 days to 60
days in paragraphs (g)(2), (4), (6), (7), (9), (10), (11), and (12) of
this AD. With this change, compliance for those specific tasks will not
be required earlier than the compliance time to revise the maintenance
program.
Request To Update Applicability
UPS requested an update to paragraph (c), ``Applicability,'' of the
proposed AD to specify airplanes ``as identified in'' Boeing 767-200/
300/300F/400ER Special Compliance Items/Airworthiness Limitations,
D622T001-9-04, dated January 2020. UPS stated that the update is needed
to clarify that each task within Boeing 767-200/300/300F/400ER Special
Compliance Items/Airworthiness Limitations, D622T001-9-04, dated
January 2020, is required only for the airplanes for which it is
identified as applicable, and not for all airplanes having L/N 1
through 1200 inclusive regardless of the task applicability.
The FAA disagrees with the request. Each task in Boeing 767-200/
300/300F/400ER Special Compliance Items/Airworthiness Limitations,
D622T001-9-04, dated January 2020, is required only for specific
airplanes, but paragraph (c), ``Applicability,'' of this AD must
include every airplane that is subject to any requirement in the AD.
This AD has not been changed with regard to this request.
Conclusion
The FAA reviewed the relevant data, considered any comments
received, and determined that air safety requires adopting this AD as
proposed. Except for minor editorial changes, and any other changes
described previously, this AD is adopted as proposed in the NPRM. None
of the changes will increase the economic burden on any operator.
Related Service Information Under 1 CFR Part 51
The FAA reviewed Boeing 767-200/300/300F/400ER Special Compliance
Items/Airworthiness Limitations, D622T001-9-04, dated January 2020.
This service information describes AWLs that include airworthiness
limitation instructions (ALIs) and critical design configuration
control limitations (CDCCLs) tasks related to fuel tank ignition
prevention and the nitrogen generation system. This service information
is reasonably available because the interested parties have access to
it through their normal course of business or by the means identified
in the ADDRESSES section.
Costs of Compliance
The FAA estimates that this AD affects 500 airplanes of U.S.
registry. The FAA estimates the following costs to comply with this AD:
The FAA has determined that revising the existing maintenance or
inspection program takes an average of 90 work-hours per operator,
although the agency recognizes that this number may vary from operator
to operator. Since operators incorporate maintenance or inspection
program changes for their affected fleet(s), the FAA has determined
that a per-operator estimate is more accurate than a per-airplane
estimate. Therefore, the FAA estimates the average total cost per
operator to be
[[Page 59011]]
$7,650 (90 work-hours x $85 per work-hour).
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.
Regulatory Findings
This AD will not have federalism implications under Executive Order
13132. This AD will not have a substantial direct effect on the States,
on the relationship between the national government and the States, or
on the distribution of power and responsibilities among the various
levels of government.
For the reasons discussed above, I certify that this AD:
(1) Is not a ``significant regulatory action'' under Executive
Order 12866,
(2) 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 Amendment
Accordingly, under the authority delegated to me by the
Administrator, the FAA amends 14 CFR part 39 as follows:
PART 39--AIRWORTHINESS DIRECTIVES
0
1. The authority citation for part 39 continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
Sec. 39.13 [Amended]
0
2. The FAA amends Sec. 39.13 by adding the following new airworthiness
directive:
2021-20-19 The Boeing Company: Amendment 39-21757; Docket No. FAA-
2021-0099; Project Identifier AD-2020-01272-T.
(a) Effective Date
This airworthiness directive (AD) is effective November 30,
2021.
(b) Affected ADs
This AD affects the ADs specified in paragraphs (b)(1) through
(7) of this AD.
(1) AD 2008-11-01 R1, Amendment 39-16145 (74 FR 68515, December
28, 2009) (AD 2008-11-01 R1).
(2) AD 2010-06-10, Amendment 39-16234 (75 FR 15322, March 29,
2010) (AD 2010-06-10).
(3) AD 2011-25-05, Amendment 39-16881 (77 FR 2442, January 18,
2012) (AD 2011-25-05).
(4) AD 2013-25-02, Amendment 39-17698 (79 FR 24541, May 1, 2014)
(AD 2013-25-02).
(5) AD 2014-08-09, Amendment 39-17833 (79 FR 24546, May 1, 2014)
(AD 2014-08-09).
(6) AD 2014-20-02, Amendment 39-17975 (79 FR 59102, October 1,
2014) (AD 2014-20-02).
(7) AD 2018-20-13, Amendment 39-19447 (83 FR 52305, October 17,
2018) (AD 2018-20-13).
(c) Applicability
This AD applies to The Boeing Company Model 767-200, -300, -
300F, and -400ER series airplanes, certificated in any category,
having line numbers (L/N) 1 through 1200 inclusive.
(d) Subject
Air Transport Association (ATA) of America Code 28, Fuel.
(e) Unsafe Condition
This AD was prompted by significant changes made to the
airworthiness limitations (AWLs) related to fuel tank ignition
prevention and the nitrogen generation system. The FAA is issuing
this AD to address the potential for ignition sources inside fuel
tanks caused by latent failures, alterations, repairs, or
maintenance actions, which, in combination with flammable fuel
vapors, 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) Maintenance or Inspection Program Revision
Within 60 days after the effective date of this AD, revise the
existing maintenance or inspection program, as applicable, to
incorporate the applicable information in Section A, including
Subsections A.1, A.2, A.3, A.4, and A.5, of Boeing 767-200/300/300F/
400ER Special Compliance Items/Airworthiness Limitations, D622T001-
9-04, dated January 2020; except as provided by paragraph (h) of
this AD. The initial compliance times for the airworthiness
limitation instructions (ALI) tasks are within the applicable
compliance times specified in paragraphs (g)(1) through (14) of this
AD:
(1) For airplanes identified in the applicability for AWL No.
28-AWL-01, ``External Wires Over Auxiliary (Center) Fuel Tank'': At
the applicable time specified in paragraph (g)(1)(i) or (ii) of this
AD.
(i) For airplanes that did not have any version of AWL No. 28-
AWL-01 in their maintenance or inspection program before the
effective date of this AD: Within 144 months since issuance of the
original airworthiness certificate or original export certificate of
airworthiness, or within 12 months after the effective date of this
AD, whichever occurs later.
(ii) For airplanes not identified in paragraph (g)(1)(i) of this
AD: Within 144 months since issuance of the original airworthiness
certificate or original export certificate of airworthiness, or
within 144 months after the most recent inspection, if any, was
performed as specified in AWL No. 28-AWL-01; whichever occurs later.
(2) For airplanes identified in the applicability for AWL No.
28-AWL-05, ``Lightning Protection--Hydraulic Line Fuel Tank
Penetration Bonding Path'': At the applicable time specified in
paragraph (g)(2)(i) or (ii) of this AD.
(i) For airplanes that did not have any version of AWL No. 28-
AWL-05 in their maintenance or inspection program before the
effective date of this AD: At the later of the times specified in
paragraphs (g)(2)(i)(A) and (B) of this AD.
(A) Within 25,000 flight hours or 72 months, whichever occurs
first since issuance of the original airworthiness certificate or
original export certificate of airworthiness.
(B) Within 60 days after the effective date of this AD.
(ii) For airplanes not identified in paragraph (g)(2)(i) of this
AD: At the later of the times specified in paragraphs (g)(2)(ii)(A)
and (B) of this AD.
(A) Within 25,000 flight hours or 72 months, whichever occurs
first since issuance of the original airworthiness certificate or
original export certificate of airworthiness.
(B) Within 25,000 flight hours or 72 months, whichever occurs
first after the most recent inspection, if any, was performed as
specified in AWL No. 28-AWL-05.
(3) For airplanes identified in the applicability for AWL No.
28-AWL-18, ``Fuel Quantity Indicating System (FQIS)--Out of Tank
Wiring Lightning Shield to Ground Termination'': At the applicable
time specified in paragraph (g)(3)(i) or (ii) of this AD.
(i) For airplanes that did not have any version of AWL No. 28-
AWL-18 in their maintenance or inspection program before the
effective date of this AD: Within 144 months since issuance of the
original airworthiness certificate or original export certificate of
airworthiness, or within 12
[[Page 59012]]
months after the effective date of this AD, whichever occurs later.
(ii) For airplanes not identified in paragraph (g)(3)(i) of this
AD: Within 144 months since issuance of the original airworthiness
certificate or original export certificate of airworthiness, or
within 144 months after the most recent inspection, if any, was
performed as specified in AWL No. 28-AWL-18; whichever occurs later.
(4) For airplanes identified in the applicability for AWL No.
28-AWL-20, ``Auxiliary (Center) Tank Override Fuel Pumps Auto
Shutoff Circuit'': At the applicable time specified in paragraph
(g)(4)(i) or (ii) of this AD.
(i) For airplanes that did not have any version of AWL No. 28-
AWL-20 in their maintenance or inspection program before the
effective date of this AD: Within 12 months since issuance of the
original airworthiness certificate or original export certificate of
airworthiness, or within 60 days after the effective date of this
AD, whichever occurs later.
(ii) For airplanes not identified in paragraph (g)(4)(i) of this
AD: At the latest of the times specified in paragraphs (g)(4)(ii)(A)
through (C) of this AD.
(A) Within 12 months since issuance of the original
airworthiness certificate or original export certificate of
airworthiness.
(B) Within 12 months after the most recent inspection, if any,
was performed as specified in AWL No. 28-AWL-20.
(C) Within 12 months after accomplishment of the actions
specified in Boeing Service Bulletin 767-28A0083 or Boeing Service
Bulletin 767-28A0084, as applicable.
(5) For airplanes identified in the applicability for AWL No.
28-AWL-21, ``AC and DC Fuel Pump Fault Current Bonding Jumper
Installation'': At the applicable time specified in paragraph
(g)(5)(i) or (ii) of this AD.
(i) For airplanes that did not have any version of AWL No. 28-
AWL-21 in their maintenance or inspection program before the
effective date of this AD: Within 72 months since issuance of the
original airworthiness certificate or original export certificate of
airworthiness, or within 6 months after the effective date of this
AD, whichever occurs later.
(ii) For airplanes not identified in paragraph (g)(5)(i) of this
AD: Within 72 months since issuance of the original airworthiness
certificate or original export certificate of airworthiness, or
within 72 months after the most recent inspection, if any, was
performed as specified in AWL No. 28-AWL-21; whichever occurs later.
(6) For airplanes identified in the applicability for AWL No.
28-AWL-27, ``Over-Current and Arcing Protection Electrical Design
Features Operation--AC Fuel Pump Ground Fault Interrupter (GFI)'':
At the applicable time specified in paragraph (g)(6)(i) or (ii) of
this AD.
(i) For airplanes that did not have any version of AWL No. 28-
AWL-27 in their maintenance or inspection program before the
effective date of this AD: Within 12 months since issuance of the
original airworthiness certificate or original export certificate of
airworthiness, or within 60 days after the effective date of this
AD, whichever occurs later.
(ii) For airplanes not identified in paragraph (g)(6)(i) of this
AD: At the latest of the times specified in paragraphs (g)(6)(ii)(A)
through (C) of this AD.
(A) Within 12 months since issuance of the original
airworthiness certificate or original export certificate of
airworthiness.
(B) Within 12 months after the most recent inspection, if any,
was performed as specified in AWL No. 28-AWL-27.
(C) Within 12 months after accomplishment of the actions
specified in Boeing Service Bulletin 767-28A0085.
(7) For airplanes identified in the applicability for AWL No.
28-AWL-28, ``Auxiliary (Center) Tank Override/Jettison Fuel Pump
Failed On Protection System'': At the applicable time specified in
paragraph (g)(7)(i) or (ii) of this AD.
(i) For airplanes that did not have any version of AWL No. 28-
AWL-28 in their maintenance or inspection program before the
effective date of this AD: Within 12 months since issuance of the
original airworthiness certificate or original export certificate of
airworthiness, or within 60 days after the effective date of this
AD, whichever occurs later.
(ii) For airplanes not identified in paragraph (g)(7)(i) of this
AD: At the latest of the times specified in paragraphs (g)(7)(ii)(A)
through (C) of this AD.
(A) Within 12 months since issuance of the original
airworthiness certificate or original export certificate of
airworthiness.
(B) Within 12 months after the most recent inspection, if any,
was performed as specified in AWL No. 28-AWL-28.
(C) Within 12 months after accomplishment of the actions
specified in Boeing Service Bulletin 767-28A0085.
(8) For airplanes identified in the applicability for AWL No.
28-AWL-35, ``Cushion Clamps and Teflon Sleeving Installed on Out-of-
Tank Wire Bundles Installed on Brackets that are Mounted Directly on
the Fuel Tanks'': At the applicable time specified in paragraph
(g)(8)(i) or (ii) of this AD.
(i) For airplanes that did not have any version of AWL No. 28-
AWL-35 in their maintenance or inspection program before the
effective date of this AD: Within 144 months since issuance of the
original airworthiness certificate or original export certificate of
airworthiness, or within 12 months after the effective date of this
AD, whichever occurs later.
(ii) For airplanes not identified in paragraph (g)(8)(i) of this
AD: At the latest of the times specified in paragraphs (g)(8)(ii)(A)
through (C) of this AD.
(A) Within 144 months since issuance of the original
airworthiness certificate or original export certificate of
airworthiness.
(B) Within 144 months after the most recent inspection, if any,
was performed as specified in AWL No. 28-AWL-35.
(C) Within 144 months after accomplishment of the actions
specified in Boeing Service Bulletin 767-57A0102.
(9) For airplanes identified in the applicability for AWL No.
28-AWL-37, ``FQIS BITE Test (Auxiliary (Center) Tank Circuit
Test)'': At the applicable time specified in paragraph (g)(9)(i) or
(ii) of this AD.
(i) For airplanes that did not have any version of AWL No. 28-
AWL-37 in their maintenance or inspection program before the
effective date of this AD: Within 750 flight hours since issuance of
the original airworthiness certificate or original export
certificate of airworthiness, or within 60 days after the effective
date of this AD, whichever occurs later.
(ii) For airplanes not identified in paragraph (g)(9)(i) of this
AD: Within 750 flight hours since issuance of the original
airworthiness certificate or original export certificate of
airworthiness, or within 750 flight hours after the most recent
inspection, if any, was performed as specified in AWL No. 28-AWL-37;
whichever occurs later.
(10) For airplanes identified in the applicability for AWL No.
28-AWL-38, ``Fuel Level Sensing System (FLSS) Dry Capacitance
Test'': At the applicable time specified in paragraph (g)(10)(i) or
(ii) of this AD.
(i) For airplanes that did not have any version of AWL No. 28-
AWL-38 in their maintenance or inspection program before the
effective date of this AD: Within 750 flight hours since issuance of
the original airworthiness certificate or original export
certificate of airworthiness, or within 60 days after the effective
date of this AD, whichever occurs later.
(ii) For airplanes not identified in paragraph (g)(10)(i) of
this AD: Within 750 flight hours since issuance of the original
airworthiness certificate or original export certificate of
airworthiness, or within 750 flight hours after the most recent
inspection, if any, was performed as specified in AWL No. 28-AWL-38;
whichever occurs later.
(11) For airplanes identified in the applicability for AWL No.
28-AWL-101, ``Engine Fuel Suction Feed Operational Test'': At the
applicable time specified in paragraph (g)(11)(i) or (ii) of this
AD.
(i) For airplanes that did not have any version of AWL No. 28-
AWL-101 in their maintenance or inspection program before the
effective date of this AD: At the later of the times specified in
paragraphs (g)(11)(i)(A) and (B) of this AD.
(A) Within 7,500 flight hours or 36 months, whichever occurs
first since issuance of the original airworthiness certificate or
original export certificate of airworthiness.
(B) Within 60 days after the effective date of this AD.
(ii) For airplanes not identified in paragraph (g)(11)(i) of
this AD: At the later of the times specified in paragraphs
(g)(11)(ii)(A) and (B) of this AD.
(A) Within 7,500 flight hours or 36 months, whichever occurs
first since issuance of the original airworthiness certificate or
original export certificate of airworthiness.
(B) Within 7,500 flight hours or 36 months, whichever occurs
first after the most recent inspection, if any, was performed as
specified in AWL No. 28-AWL-101.
(12) For airplanes identified in the applicability for AWL No.
28-AWL-102, ``Fuel Quantity Indicating System (FQIS)--
[[Page 59013]]
Low Fuel and Fuel Config Indication Test'': At the applicable time
specified in paragraph (g)(12)(i) or (ii) of this AD.
(i) For airplanes that did not have any version of AWL No. 28-
AWL-102 in their maintenance or inspection program before the
effective date of this AD: Within 750 flight hours since issuance of
the original airworthiness certificate or original export
certificate of airworthiness; or within 60 days after the effective
date of this AD, whichever occurs later.
(ii) For airplanes not identified in paragraph (g)(12)(i) of
this AD: At the latest of the times specified in paragraphs
(g)(12)(ii)(A) through (C) of this AD.
(A) Within 750 flight hours since issuance of the original
airworthiness certificate or original export certificate of
airworthiness.
(B) Within 750 flight hours after the most recent inspection, if
any, was performed as specified in AWL No. 28-AWL-102.
(C) Within 750 flight hours after accomplishment of the actions
specified in Boeing Service Bulletin 767-31-0295 or Boeing Service
Bulletin 767-31-0302, as applicable.
(13) For airplanes identified in the applicability for AWL No.
47-AWL-04, ``Nitrogen Generation System (NGS)--Nitrogen-Enriched Air
(NEA) Distribution Ducting'': At the applicable time specified in
paragraph (g)(13)(i) or (ii) of this AD.
(i) For airplanes that did not have any version of AWL No. 47-
AWL-04 in their maintenance or inspection program before the
effective date of this AD: Within the applicable interval specified
in AWL No. 47-AWL-04 since issuance of the original airworthiness
certificate or original export certificate of airworthiness, or
within 4 months after the effective date of this AD, whichever
occurs later.
(ii) For airplanes not identified in paragraph (g)(13)(i) of
this AD: Within the applicable interval specified in AWL No. 47-AWL-
04 since issuance of the original airworthiness certificate or
original export certificate of airworthiness, or within that
applicable interval since the most recent inspection, if any, was
performed as specified in AWL No. 47-AWL-04; whichever occurs later.
(14) For airplanes identified in the applicability for AWL No.
47-AWL-05, ``Nitrogen Generation System (NGS)--Cross Vent Check
Valve'': At the applicable time specified in paragraph (g)(14)(i) or
(ii) of this AD.
(i) For airplanes that did not have any version of AWL No. 47-
AWL-05 in their maintenance or inspection program before the
effective date of this AD: Within the applicable interval specified
in AWL No. 47-AWL-05 since issuance of the original airworthiness
certificate or original export certificate of airworthiness, or
within 4 months after the effective date of this AD, whichever
occurs later.
(ii) For airplanes not identified in paragraph (g)(14)(i) of
this AD: Within the applicable interval specified in AWL No. 47-AWL-
05 since issuance of the original airworthiness certificate or
original export certificate of airworthiness, or within that
applicable interval since the most recent inspection, if any, was
performed as specified in AWL No. 47-AWL-05; whichever occurs later.
(h) Additional Acceptable Wire Types and Sleeving
As an option, during accomplishment of the actions required by
paragraph (g) of this AD, the changes specified in paragraphs (h)(1)
and (2) of this AD are acceptable.
(1) Where AWL No. 28-AWL-09 identifies wire types BMS 13-48, BMS
13-58, and BMS 13-60, the following acceptable wire types and cables
can be added to AWL No. 28-AWL-09: MIL-W-22759/16, SAE AS22759/16
(formerly M22759/16), MIL-W-22759/32, SAE AS22759/32 (formerly
M22759/32), MIL-W-22759/34, SAE AS22759/34 (formerly M22759/34),
MIL-W-22759/41, SAE AS22759/41 (formerly M22759/41), MIL-W-22759/86,
SAE AS22759/86 (formerly M22759/86), MIL-W-22759/87, SAE AS22759/87
(formerly M22759/87), MIL-W-22759/92, and SAE AS22759/92 (formerly
M22759/92); and MIL-C-27500 and NEMA WC 27500 cables that are
constructed from these military or SAE specification wire types, as
applicable.
(2) Where AWL No. 28-AWL-09 identifies TFE-2X Standard wall for
wire sleeving, the following sleeving materials are acceptable:
Roundit 2000NX and Varglas Type HO, HP, or HM, Grade A.
(i) No Alternative Actions, Intervals, or Critical Design Configuration
Control Limitations (CDCCLs)
After the existing maintenance or inspection program has been
revised as required by paragraph (g) of this AD, no alternative
actions (e.g., inspections), intervals, or CDCCLs may be used unless
the actions, intervals, and CDCCLs are approved as an alternative
method of compliance (AMOC) in accordance with the procedures
specified in paragraph (k) of this AD.
(j) Terminating Action for Certain AD Requirements
Accomplishment of the revision required by paragraph (g) of this
AD terminates the requirements specified in paragraphs (j)(1)
through (7) of this AD for that airplane:
(1) The revision required by paragraphs (g) and (h) of AD 2008-
11-01 R1.
(2) The revision required by paragraph (h) of AD 2010-06-10.
(3) The revision required by paragraph (k) of AD 2011-25-05.
(4) The revision required by paragraph (n) of AD 2013-25-02.
(5) The revision required by paragraph (g) of AD 2014-08-09.
(6) The revision required by paragraph (h) of AD 2014-20-02.
(7) The revision required by paragraphs (i)(3)(i) and (ii) of AD
2018-20-13.
(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 responsible Flight Standards 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 responsible Flight Standards 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.
(l) Related Information
For more information about this AD, contact Douglas Mansell,
Aerospace Engineer, Propulsion Section, FAA, Seattle ACO Branch,
2200 South 216th St., Des Moines, WA 98198; phone and fax: 206-231-
3875; email: [email protected].
(m) Material Incorporated by Reference
(1) The Director of the Federal Register approved the
incorporation by reference (IBR) of the service information listed
in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51.
(2) You must use this service information as applicable to do
the actions required by this AD, unless the AD specifies otherwise.
(i) Boeing 767-200/300/300F/400ER Special Compliance Items/
Airworthiness Limitations, D622T001-9-04, dated January 2020.
(ii) [Reserved]
(3) 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.
(4) You may view this service information at the FAA,
Airworthiness Products Section, Operational Safety Branch, 2200
South 216th St., Des Moines, WA. For information on the availability
of this material at the FAA, call 206-231-3195.
(5) You may view this service information that is incorporated
by reference at the National Archives and Records Administration
(NARA). For information on the availability of this material at
NARA, email [email protected], or go to: https://www.archives.gov/federal-register/cfr/ibr-locations.html.
Issued on September 23, 2021.
Lance T. Gant,
Director, Compliance & Airworthiness Division, Aircraft Certification
Service.
[FR Doc. 2021-23268 Filed 10-25-21; 8:45 am]
BILLING CODE 4910-13-P
