Airworthiness Directives; The Boeing Company Airplanes, 48927-48930 [2018-20918]
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Federal Register / Vol. 83, No. 189 / Friday, September 28, 2018 / Rules and Regulations
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2018–0504; Product
Identifier 2018–NM–046–AD; Amendment
39–19433; AD 2018–19–32]
RIN 2120–AA64
Airworthiness Directives; The Boeing
Company Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule.
AGENCY:
We are adopting a new
airworthiness directive (AD) for all The
Boeing Company Model 707, 720, and
720B series airplanes. This AD was
prompted by a report indicating that a
fracture of the midspar fitting resulted
in the separation of the inboard strut
and engine from the airplane, and a
determination that existing inspections
are not sufficient for timely detection of
cracking. This AD requires repetitive
inspections of certain nacelle strut spar
and overwing fittings, and diagonal
braces and associated fittings;
replacement of the diagonal brace
assembly on certain airplanes; and
applicable related investigative and
corrective actions. We are issuing this
AD to address the unsafe condition on
these products.
DATES: This AD is effective November 2,
2018.
The Director of the Federal Register
approved the incorporation by reference
of certain publications listed in this AD
as of November 2, 2018.
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, 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–2018–
0504.
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SUMMARY:
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–2018–
0504; or in person at Docket Operations
between 9 a.m. and 5 p.m., Monday
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17:35 Sep 27, 2018
Jkt 244001
through Friday, except Federal holidays.
The AD docket contains this final rule,
the regulatory evaluation, any
comments received, and other
information. The address for Docket
Operations (phone: 800–647–5527) 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:
Jeffrey Chang, Aerospace Engineer,
Propulsion Section, FAA, Los Angeles
ACO Branch, 3960 Paramount
Boulevard, Lakewood, CA 90712–4137;
phone: 562–627–5263; fax: 562–627–
5210; email: jeffrey.chang@faa.gov; or
George Garrido, Aerospace Engineer,
Airframe Section, FAA, Los Angeles
ACO Branch, 3960 Paramount
Boulevard, Lakewood, CA 90712–4137;
phone: 562–627–5232; fax: 562–627–
5210; email george.garrido@faa.gov.
SUPPLEMENTARY INFORMATION:
Discussion
We issued a notice of proposed
rulemaking (NPRM) to amend 14 CFR
part 39 by adding an AD that would
apply to all The Boeing Company Model
707, 720, and 720B series airplanes. The
NPRM published in the Federal
Register on June 7, 2018 (83 FR 26383).
The NPRM was prompted by a report
indicating that a fracture of the midspar
fitting resulted in the separation of the
inboard strut and engine from the
airplane, and a determination that
existing inspections are not sufficient
for timely detection of cracking. The
NPRM proposed to require repetitive
inspections of certain nacelle strut spar
and overwing fittings, and diagonal
braces and associated fittings;
replacement of the diagonal brace
assembly on certain airplanes; and
applicable related investigative and
corrective actions.
We are issuing this AD to address
cracks, which if not detected and
corrected, could grow beyond a critical
length, allowing the strut fitting to fail
and reducing the structural integrity of
the nacelle. This, in combination with
damage to adjacent attachment
structure, could result in the loss of an
engine from the airplane.
Comments
We gave the public the opportunity to
participate in developing this final rule.
The following presents the comment
received on the NPRM and the FAA’s
response.
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48927
Request To Clarify Service Information
Used for Oversizing Certain Holes
Boeing requested that we revise
paragraph (k) of the proposed AD to
specify outboard diagonal brace end
fitting (forward or aft) attach holes that
have been oversized as specified in
Boeing 707 Alert Service Bulletin
A3364, ‘‘Revision 3, dated May 29,
1981,’’ rather than ‘‘Revision 4, dated
February 21, 2017.’’ Boeing noted that
Boeing 707 Alert Service Bulletin
A3364, Revision 4, dated February 21,
2017, does not contain instructions for
oversizing the attach holes, but instead
refers to oversizing done as specified in
Revision 3. Boeing added that, as
written, the proposed AD would not
require operators to replace a diagonal
brace assembly with attach holes that
were oversized as specified in Boeing
707 Alert Service Bulletin A3364,
Revision 3, dated May 29, 1981,
potentially allowing an unsafe condition
to continue.
We agree with the commenter’s
request. We have revised paragraph (k)
of this AD to specify ‘‘. . . outboard
diagonal brace end fitting (forward or
aft) attach holes have been oversized as
specified in Boeing 707 Alert Service
Bulletin A3364, Revision 3, dated May
29, 1981.’’
Conclusion
We reviewed the relevant data,
considered the comment received, and
determined that air safety and the
public interest require adopting this
final rule with the change described
previously and minor editorial changes.
We have determined that these minor
changes:
• Are consistent with the intent that
was proposed in the NPRM for
addressing the unsafe condition; and
• Do not add any additional burden
upon the public than was already
proposed in the NPRM.
We also determined that these
changes will not increase the economic
burden on any operator or increase the
scope of this final rule.
Related Service Information Under 1
CFR Part 51
We reviewed the following service
information.
• Boeing 707 Alert Service Bulletin
A3364, Revision 4, dated February 21,
2017. This service information describes
procedures for repetitive detailed
inspections of the diagonal brace tube
for any crack; repetitive detailed
inspections and high frequency eddy
current (HFEC) inspections of the
nacelle strut diagonal brace end fittings,
forward mating fitting, and aft mating
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Federal Register / Vol. 83, No. 189 / Friday, September 28, 2018 / Rules and Regulations
fitting for any crack; an alternative dye
penetrant inspection of vertical webs on
aft mating fitting for any crack; an HFEC
inspection of the diagonal brace tube for
any crack; and corrective actions.
• Boeing 707 Alert Service Bulletin
A3365, Revision 3, dated March 9, 2017.
This service information describes
procedures for repetitive detailed,
HFEC, and ultrasonic inspections of the
overwing support fittings for any crack
at the bolt hole forward of the wing
front spar and at the holes for the four
fasteners attaching the fitting to the
spar, and related investigative and
corrective actions.
• Boeing 707 Alert Service Bulletin
A3514, Revision 1, dated November 9,
2016. This service information describes
procedures for repetitive detailed and
surface HFEC inspections of the front
spar fittings at nacelle struts numbers 1,
2, 3, and 4 for cracks, and replacement
of cracked front spar fittings.
This service information is reasonably
available because the interested parties
have access to it through their normal
course of business or by the means
identified in the ADDRESSES section.
Costs of Compliance
We estimate that this AD affects 65
airplanes of U.S. registry. We estimate
the following costs to comply with this
AD:
ESTIMATED COSTS
Action
Labor cost
Detailed inspections per Service Bulletin
A3364, Revision 4.
HFEC inspections per Service Bulletin A3364,
Revision 4.
Inspections per Service Bulletin A3365, Revision 3.
Detailed inspections per Service Bulletin
A3514, Revision 1.
HFEC inspections per Service Bulletin A3514,
Revision 1.
36 work-hours × $85
inspection cycle.
128 work-hours × $85
inspection cycle.
20 work-hours × $85
inspection cycle.
12 work-hours × $85
inspection cycle.
32 work-hours × $85
inspection cycle.
We estimate that any necessary
replacement of affected fittings would
take about 96 work-hours for a cost of
$8,160 per fitting. We have received no
definitive data on the parts costs of the
affected fittings. We have no way of
determining the number of aircraft that
might need this replacement.
We have received no definitive data
that would enable us to provide cost
estimates for the on-condition actions
specified in this AD.
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Authority for This Rulemaking
Title 49 of the United States Code
specifies the FAA’s authority to issue
rules on aviation safety. Subtitle I,
section 106, describes the authority of
the FAA Administrator. Subtitle VII:
Aviation Programs, describes in more
detail the scope of the Agency’s
authority.
We are issuing this rulemaking under
the authority described in Subtitle VII,
Part A, Subpart III, Section 44701:
‘‘General requirements.’’ Under that
section, Congress charges the FAA with
promoting safe flight of civil aircraft in
air commerce by prescribing regulations
for practices, methods, and procedures
the Administrator finds necessary for
safety in air commerce. This regulation
is within the scope of that authority
because it addresses an unsafe condition
that is likely to exist or develop on
products identified in this rulemaking
action.
This 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
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Jkt 244001
Parts cost
Cost per product
per hour = $3,060 per
$0
per hour = $10,880 per
0
per hour = $1,700 per
0
per hour = $1,020 per
0
per hour = $2,720 per
0
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
This AD will not have federalism
implications under Executive Order
13132. This AD will not have a
substantial direct effect on the States, on
the relationship between the national
government and the States, or on the
distribution of power and
responsibilities among the various
levels of government.
For the reasons discussed above, I
certify that this AD:
(1) Is not a ‘‘significant regulatory
action’’ under Executive Order 12866,
(2) Is not a ‘‘significant rule’’ under
DOT Regulatory Policies and Procedures
(44 FR 11034, February 26, 1979),
(3) Will not affect intrastate aviation
in Alaska, and
(4) Will not have a significant
economic impact, positive or negative,
on a substantial number of small entities
under the criteria of the Regulatory
Flexibility Act.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation
safety, Incorporation by reference,
Safety.
Adoption of the Amendment
Accordingly, under the authority
delegated to me by the Administrator,
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$3,060 per inspection
cycle.
$10,880 per inspection
cycle.
$1,700 per inspection
cycle.
$1,020 per inspection
cycle.
$2,720 per inspection
cycle.
Cost on U.S. operators
$198,900 per inspection
cycle.
$707,200 per inspection
cycle.
$110,500 per inspection
cycle.
$66,300 per inspection
cycle.
$176,800 per inspection
cycle.
the FAA amends 14 CFR part 39 as
follows:
PART 39—AIRWORTHINESS
DIRECTIVES
1. The authority citation for part 39
continues to read as follows:
■
Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13
[Amended]
2. The FAA amends § 39.13 by adding
the following new airworthiness
directive (AD):
■
2018–19–32 The Boeing Company:
Amendment 39–19433; Docket No.
FAA–2018–0504; Product Identifier
2018–NM–046–AD.
(a) Effective Date
This AD is effective November 2, 2018.
(b) Affected ADs
This AD affects AD 82–24–03, Amendment
39–4496 (47 FR 51099, November 12, 1982)
(‘‘AD 82–24–03’’) and AD 2005–08–15,
Amendment 39–14067 (70 FR 21136, April
25, 2005) (‘‘AD 2005–08–15’’).
(c) Applicability
This AD applies to all The Boeing
Company Model 707–100 Long Body, –200,
–100B Long Body, and –100B Short Body
series airplanes; Model 707–300, –300B,
–300C, and –400 series airplanes; and Model
720 and 720B series airplanes; certificated in
any category.
(d) Subject
Air Transport Association (ATA) of
America Code 54, Nacelles/pylons.
(e) Unsafe Condition
This AD was prompted by a report
indicating that a fracture of the midspar
fitting resulted in the separation of the
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inboard strut and engine from the airplane,
and a determination that existing inspections
for other nacelle strut fittings are not
sufficient for timely detection of cracking.
We are issuing this AD to address cracks,
which if not detected and corrected, could
grow beyond a critical length, allowing the
strut fitting to fail and reducing the structural
integrity of the nacelle. This, in combination
with damage to adjacent attachment
structure, could result in the loss of an
engine from the airplane.
(f) Compliance
Comply with this AD within the
compliance times specified, unless already
done.
(g) Repetitive Detailed Inspections of the
Front Spar Fittings at Nacelle Struts
Numbers 1, 2, 3, and 4
Prior to the accumulation of 3,500 total
flight hours; within 700 flight hours after the
most recent inspection specified in Boeing
707 Alert Service Bulletin A3514, dated July
29, 2004, was done; or within three months
after the effective date of this AD; whichever
occurs later: Do a detailed inspection for
cracking of the front spar fittings at nacelle
struts numbers 1, 2, 3, and 4, in accordance
with the Accomplishment Instructions of
Boeing 707 Alert Service Bulletin A3514,
Revision 1, dated November 9, 2016. If any
cracking is found, before further flight,
replace the affected fitting, in accordance
with the Accomplishment Instructions of
Boeing 707 Alert Service Bulletin A3514,
Revision 1, dated November 9, 2016. Repeat
the inspections thereafter at intervals not to
exceed 700 flight hours.
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(h) Repetitive Surface High Frequency Eddy
Current (HFEC) Inspections of the Aft Lugs
on the Front Spar Fittings at Nacelle Struts
Numbers 1, 2, 3, and 4
Within 1,500 flight cycles or 48 months
after the most recent detailed inspection
required by paragraph (g) of this AD was
done, whichever occurs first, do a surface
HFEC inspection for cracking of the aft lugs
on the front spar fittings at nacelle struts
numbers 1, 2, 3, and 4, and do all applicable
corrective actions, in accordance with the
Accomplishment Instructions of Boeing 707
Alert Service Bulletin A3514, Revision 1,
dated November 9, 2016, except as required
by paragraph (l)(4) of this AD. Do all
applicable corrective actions before further
flight. Repeat the inspection thereafter at
intervals not to exceed 1,500 flight cycles or
48 months, whichever occurs first.
(i) Repetitive Inspections of the Overwing
Support Fitting at Nacelle Struts Numbers 1,
2, 3, and 4
At the times specified in paragraph 1.E.,
‘‘Compliance,’’ of Boeing 707 Alert Service
Bulletin A3365, Revision 3, dated March 9,
2017, except as required by paragraph (l)(1)
of this AD: Do the inspections specified in
paragraphs (i)(1) through (i)(3) of this AD and
do all applicable related investigative and
corrective actions, in accordance with the
Accomplishment Instructions of Boeing 707
Alert Service Bulletin A3365, Revision 3,
dated March 9, 2017, except as required by
paragraph (l)(3) of this AD. Do all applicable
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related investigative and corrective actions
before further flight. Repeat the inspections
thereafter at the applicable time specified in
paragraph 1.E., ‘‘Compliance,’’ of Boeing 707
Alert Service Bulletin A3365, Revision 3,
dated March 9, 2017.
(1) Do a detailed inspection for any crack
at all five holes in the overwing support
fitting, and at the flange radii.
(2) Do the inspection specified in
paragraph (i)(2)(i) or (i)(2)(ii) of this AD.
(i) Do a surface HFEC inspection for any
crack in the overwing support fitting around
the hole immediately forward of the spar
chord, with the bolt in place, and at the
flange radii.
(ii) Do an open hole HFEC inspection for
any crack in the overwing support fitting at
the hole immediately forward of the spar
chord.
(3) Do the inspection specified in
paragraph (i)(3)(i) or (i)(3)(ii) of this AD.
(i) Do an ultrasonic inspection for any
crack in the overwing support fitting around
the four holes common to the fitting and the
spar chord, with the bolts in place.
(ii) Do a surface HFEC inspection for any
crack in the overwing support fitting around
the four holes common to the fitting and the
spar chord, with the bolts in place.
(j) Inspections of the Nacelle Strut Diagonal
Braces and Associated Fittings
For airplanes with nacelle strut diagonal
braces and associated fittings which have
accumulated 7,500 flight cycles or more: At
the applicable times specified in paragraph
1.E., ‘‘Compliance’’ of Boeing 707 Alert
Service Bulletin A3364, Revision 4, dated
February 21, 2017, except as required by
paragraph (l)(2) of this AD, do the
inspections specified in paragraphs (j)(1)
through (j)(3) of this AD. Repeat the
inspections thereafter at the applicable
intervals specified in tables 1, 2, 3, and 4 of
paragraph 1.E., ‘‘Compliance,’’ of Boeing 707
Alert Service Bulletin A3364, Revision 4,
dated February 21, 2017. If any crack is
found during any inspection required by this
paragraph, before further flight, do all
applicable corrective actions, in accordance
with the Accomplishment Instructions of
Boeing 707 Alert Service Bulletin A3364,
Revision 4, dated February 21, 2017, except
as required by paragraph (l)(3) of this AD.
(1) Do a detailed inspection of the nacelle
strut diagonal brace end fittings, diagonal
brace tube, forward mating fitting, and aft
mating fitting for any crack.
(2) Do HFEC inspections of the nacelle
strut diagonal brace end fittings, forward
mating fitting, and aft mating fitting for any
crack. As an alternative for the aft mating
fitting, do a dye penetrant inspection of
vertical webs on aft mating fitting for any
crack.
(3) Do an HFEC inspection of the diagonal
brace tube for any crack.
(k) Replacement
For Group 3, 4, and 6 airplanes as
identified in Boeing 707 Alert Service
Bulletin A3364, Revision 4, dated February
21, 2017, on which the outboard diagonal
brace end fitting (forward or aft) attach holes
have been oversized as specified in Boeing
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48929
707 Alert Service Bulletin A3364, Revision 3,
dated May 29, 1981: Within 1,000 flight
cycles after the effective date of this AD,
replace the diagonal brace assembly, in
accordance with Figure 3 of Boeing 707 Alert
Service Bulletin A3364, Revision 4, dated
February 21, 2017.
(l) Exceptions to Service Information
Specifications
(1) For purposes of determining
compliance with the requirements of this AD:
Where Boeing 707 Alert Service Bulletin
A3365, Revision 3, dated March 9, 2017, uses
the phrase ‘‘the Revision 3 date of this
service bulletin,’’ this AD requires using ‘‘the
effective date of this AD.’’
(2) For purposes of determining
compliance with the requirements of this AD:
Where Boeing 707 Alert Service Bulletin
A3364, Revision 4, dated February 21, 2017,
uses the phrase ‘‘the Revision 4 date of this
service bulletin,’’ this AD requires using ‘‘the
effective date of this AD.’’
(3) Where Boeing 707 Alert Service
Bulletin A3364, Revision 4, dated February
21, 2017; and Boeing 707 Alert Service
Bulletin A3365, Revision 3, dated March 9,
2017; specify contacting Boeing: This AD
requires repair using a method approved in
accordance with the procedures specified in
paragraph (o) of this AD.
(4) Where Boeing 707 Alert Service
Bulletin A3514, Revision 1, dated November
9, 2016, specifies contacting Boeing for
replacement instructions: This AD requires
replacement using a method approved in
accordance with the procedures specified in
paragraph (o) of this AD.
(m) Terminating Action for Other ADs
(1) Accomplishing the initial inspections
required by paragraph (j) of this AD
terminates all requirements of AD 82–24–03.
(2) Accomplishing the initial inspections
required by paragraph (g) of this AD,
terminates all requirements of AD 2005–08–
15.
(n) Parts Installation Prohibition
As of the effective date of this AD, no
person may install, on any airplane, a front
spar fitting having a part number other than
the part numbers specified in paragraph
2.C.2. of Boeing 707 Alert Service Bulletin
A3514, Revision 1, dated November 9, 2016.
(o) Alternative Methods of Compliance
(AMOCs)
(1) The Manager, Los Angeles 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(s) identified in paragraph (p)(1) of
this AD. Information may be emailed to: 9ANM-LAACO-AMOC-Requests@faa.gov.
(2) Before using any approved AMOC,
notify your appropriate principal inspector,
or lacking a principal inspector, the manager
of the local flight standards district office/
certificate holding district office.
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Federal Register / Vol. 83, No. 189 / Friday, September 28, 2018 / Rules and Regulations
(3) An AMOC that provides an acceptable
level of safety may be used for any repair,
modification, replacement, or alteration
required by this AD if it is approved by the
Boeing Commercial Airplanes Organization
Designation Authorization (ODA) that has
been authorized by the Manager, Los Angeles
ACO Branch, FAA, to make those findings.
To be approved, the repair method,
modification deviation, replacement
deviation, or alteration deviation must meet
the certification basis of the airplane, and the
approval must specifically refer to this AD.
(p) Related Information
(1) For more information about this AD,
contact Jeffrey Chang, Aerospace Engineer,
Propulsion Section, FAA, Los Angeles ACO
Branch, 3960 Paramount Boulevard,
Lakewood, CA 90712–4137; phone: 562–627–
5263; fax: 562–627–5210; email:
jeffrey.chang@faa.gov; or George Garrido,
Aerospace Engineer, Airframe Section, FAA,
Los Angeles ACO Branch, 3960 Paramount
Boulevard, Lakewood, CA 90712–4137;
phone: 562–627–5232; fax: 562–627–5210;
email george.garrido@faa.gov.
(2) Service information identified in this
AD that is not incorporated by reference is
available at the addresses specified in
paragraphs (q)(3) and (q)(4) of this AD.
(q) Material Incorporated by Reference
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(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 707 Alert Service Bulletin
A3364, Revision 4, dated February 21, 2017.
(ii) Boeing 707 Alert Service Bulletin
A3365, Revision 3, dated March 9, 2017.
(iii) Boeing 707 Alert Service Bulletin
A3514, Revision 1, dated November 9, 2016.
(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, 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.
(5) You may view this service information
that is incorporated by reference at the
National Archives and Records
Administration (NARA). For information on
the availability of this material at NARA, call
202–741–6030, or go to: https://
www.archives.gov/federal-register/cfr/ibrlocations.html.
Issued in Des Moines, Washington, on
September 17, 2018.
John P. Piccola,
Acting Director, System Oversight Division,
Aircraft Certification Service.
[FR Doc. 2018–20918 Filed 9–27–18; 8:45 am]
BILLING CODE 4910–13–P
VerDate Sep<11>2014
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2018–0491; Product
Identifier 2017–NM–158–AD; Amendment
39–19432; AD 2018–19–31]
RIN 2120–AA64
Airworthiness Directives; Airbus SAS
Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
AGENCY:
We are adopting a new
airworthiness directive (AD) for all
Airbus SAS Model A310 series
airplanes. This AD was prompted by a
determination that new or more
restrictive maintenance requirements
and airworthiness limitations are
necessary. This AD requires revising the
maintenance or inspection program, as
applicable, to incorporate new or more
restrictive maintenance requirements
and airworthiness limitations. We are
issuing this AD to address the unsafe
condition on these products.
DATES: This AD is effective November 2,
2018.
The Director of the Federal Register
approved the incorporation by reference
of a certain publication listed in this AD
as of November 2, 2018.
ADDRESSES: For service information
identified in this final rule, contact
Airbus SAS, Airworthiness Office—
EAW, Rond-Point Emile Dewoitine No:
2, 31700 Blagnac Cedex, France; phone:
+33 5 61 93 36 96; fax: +33 5 61 93 44
51; email: account.airworth-eas@
airbus.com; internet: https://
www.airbus.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–2018–
0491.
SUMMARY:
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–2018–
0491; 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,
the regulatory evaluation, any
comments received, and other
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Sfmt 4700
information. The address for Docket
Operations (phone: 800–647–5527) 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: Dan
Rodina, Aerospace Engineer,
International Section, Transport
Standards Branch, FAA, 2200 South
216th St., Des Moines, WA 98198;
phone and fax: 206–231–3225.
SUPPLEMENTARY INFORMATION:
Discussion
We issued a notice of proposed
rulemaking (NPRM) to amend 14 CFR
part 39 by adding an AD that would
apply to all Airbus SAS Model A310
series airplanes. The NPRM published
in the Federal Register on June 1, 2018
(83 FR 25412). The NPRM was
prompted by a determination that new
or more restrictive maintenance
requirements and airworthiness
limitations are necessary. The NPRM
proposed to require revising the
maintenance or inspection program, as
applicable, to incorporate new or more
restrictive maintenance requirements
and airworthiness limitations.
We are issuing this AD to address
prevent fatigue cracking, damage, or
corrosion in principal structural
elements, which could result in reduced
structural integrity of the airplane.
The European Aviation Safety Agency
(EASA), which is the Technical Agent
for the Member States of the European
Union, has issued EASA AD 2017–0206,
dated October 12, 2017 (referred to after
this as the Mandatory Continuing
Airworthiness Information, or ‘‘the
MCAI’’), to correct an unsafe condition
for all Airbus Model A310 series
airplanes. The MCAI states:
The airworthiness limitations for the
Airbus A310 aeroplanes, which are approved
by EASA, are currently defined and
published in the Airbus A310 Airworthiness
Limitations Section (ALS) documents. The
Damage Tolerant Airworthiness Limitation
Items are specified in the A310 ALS Part 2.
These instructions have been identified as
mandatory for continuing airworthiness.
Failure to accomplish these instructions
could result in an unsafe condition.
EASA previously issued AD 2016–0217
[which corresponds to FAA AD 2017–21–08,
Amendment 39–19079 (82 FR 48904, October
23, 2017) (‘‘AD 2017–21–08’’)] to require
compliance with the maintenance
requirements and associated airworthiness
limitations defined in Airbus A310 ALS Part
2 Revision 01, Variation 1.1 and Variation
1.2.
Since that [EASA] AD was issued, new or
more restrictive maintenance requirements
and associated airworthiness limitations
E:\FR\FM\28SER1.SGM
28SER1
]]>Agencies
[Federal Register Volume 83, Number 189 (Friday, September 28, 2018)]
[Rules and Regulations]
[Pages 48927-48930]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2018-20918]
[[Page 48927]]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2018-0504; Product Identifier 2018-NM-046-AD; Amendment
39-19433; AD 2018-19-32]
RIN 2120-AA64
Airworthiness Directives; The Boeing Company Airplanes
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Final rule.
-----------------------------------------------------------------------
SUMMARY: We are adopting a new airworthiness directive (AD) for all The
Boeing Company Model 707, 720, and 720B series airplanes. This AD was
prompted by a report indicating that a fracture of the midspar fitting
resulted in the separation of the inboard strut and engine from the
airplane, and a determination that existing inspections are not
sufficient for timely detection of cracking. This AD requires
repetitive inspections of certain nacelle strut spar and overwing
fittings, and diagonal braces and associated fittings; replacement of
the diagonal brace assembly on certain airplanes; and applicable
related investigative and corrective actions. We are issuing this AD to
address the unsafe condition on these products.
DATES: This AD is effective November 2, 2018.
The Director of the Federal Register approved the incorporation by
reference of certain publications listed in this AD as of November 2,
2018.
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, 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-2018-
0504.
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-2018-
0504; 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, the regulatory evaluation, any comments received, and
other information. The address for Docket Operations (phone: 800-647-
5527) 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: Jeffrey Chang, Aerospace Engineer,
Propulsion Section, FAA, Los Angeles ACO Branch, 3960 Paramount
Boulevard, Lakewood, CA 90712-4137; phone: 562-627-5263; fax: 562-627-
5210; email: [email protected]; or George Garrido, Aerospace
Engineer, Airframe Section, FAA, Los Angeles ACO Branch, 3960 Paramount
Boulevard, Lakewood, CA 90712-4137; phone: 562-627-5232; fax: 562-627-
5210; email [email protected].
SUPPLEMENTARY INFORMATION:
Discussion
We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR
part 39 by adding an AD that would apply to all The Boeing Company
Model 707, 720, and 720B series airplanes. The NPRM published in the
Federal Register on June 7, 2018 (83 FR 26383). The NPRM was prompted
by a report indicating that a fracture of the midspar fitting resulted
in the separation of the inboard strut and engine from the airplane,
and a determination that existing inspections are not sufficient for
timely detection of cracking. The NPRM proposed to require repetitive
inspections of certain nacelle strut spar and overwing fittings, and
diagonal braces and associated fittings; replacement of the diagonal
brace assembly on certain airplanes; and applicable related
investigative and corrective actions.
We are issuing this AD to address cracks, which if not detected and
corrected, could grow beyond a critical length, allowing the strut
fitting to fail and reducing the structural integrity of the nacelle.
This, in combination with damage to adjacent attachment structure,
could result in the loss of an engine from the airplane.
Comments
We gave the public the opportunity to participate in developing
this final rule. The following presents the comment received on the
NPRM and the FAA's response.
Request To Clarify Service Information Used for Oversizing Certain
Holes
Boeing requested that we revise paragraph (k) of the proposed AD to
specify outboard diagonal brace end fitting (forward or aft) attach
holes that have been oversized as specified in Boeing 707 Alert Service
Bulletin A3364, ``Revision 3, dated May 29, 1981,'' rather than
``Revision 4, dated February 21, 2017.'' Boeing noted that Boeing 707
Alert Service Bulletin A3364, Revision 4, dated February 21, 2017, does
not contain instructions for oversizing the attach holes, but instead
refers to oversizing done as specified in Revision 3. Boeing added
that, as written, the proposed AD would not require operators to
replace a diagonal brace assembly with attach holes that were oversized
as specified in Boeing 707 Alert Service Bulletin A3364, Revision 3,
dated May 29, 1981, potentially allowing an unsafe condition to
continue.
We agree with the commenter's request. We have revised paragraph
(k) of this AD to specify ``. . . outboard diagonal brace end fitting
(forward or aft) attach holes have been oversized as specified in
Boeing 707 Alert Service Bulletin A3364, Revision 3, dated May 29,
1981.''
Conclusion
We reviewed the relevant data, considered the comment received, and
determined that air safety and the public interest require adopting
this final rule with the change described previously and minor
editorial changes. We have determined that these minor changes:
Are consistent with the intent that was proposed in the
NPRM for addressing the unsafe condition; and
Do not add any additional burden upon the public than was
already proposed in the NPRM.
We also determined that these changes will not increase the
economic burden on any operator or increase the scope of this final
rule.
Related Service Information Under 1 CFR Part 51
We reviewed the following service information.
Boeing 707 Alert Service Bulletin A3364, Revision 4, dated
February 21, 2017. This service information describes procedures for
repetitive detailed inspections of the diagonal brace tube for any
crack; repetitive detailed inspections and high frequency eddy current
(HFEC) inspections of the nacelle strut diagonal brace end fittings,
forward mating fitting, and aft mating
[[Page 48928]]
fitting for any crack; an alternative dye penetrant inspection of
vertical webs on aft mating fitting for any crack; an HFEC inspection
of the diagonal brace tube for any crack; and corrective actions.
Boeing 707 Alert Service Bulletin A3365, Revision 3, dated
March 9, 2017. This service information describes procedures for
repetitive detailed, HFEC, and ultrasonic inspections of the overwing
support fittings for any crack at the bolt hole forward of the wing
front spar and at the holes for the four fasteners attaching the
fitting to the spar, and related investigative and corrective actions.
Boeing 707 Alert Service Bulletin A3514, Revision 1, dated
November 9, 2016. This service information describes procedures for
repetitive detailed and surface HFEC inspections of the front spar
fittings at nacelle struts numbers 1, 2, 3, and 4 for cracks, and
replacement of cracked front spar fittings.
This service information is reasonably available because the
interested parties have access to it through their normal course of
business or by the means identified in the ADDRESSES section.
Costs of Compliance
We estimate that this AD affects 65 airplanes of U.S. registry. We
estimate the following costs to comply with this AD:
Estimated Costs
--------------------------------------------------------------------------------------------------------------------------------------------------------
Action Labor cost Parts cost Cost per product Cost on U.S. operators
--------------------------------------------------------------------------------------------------------------------------------------------------------
Detailed inspections per Service 36 work-hours x $85 per $0 $3,060 per inspection cycle........ $198,900 per inspection cycle.
Bulletin A3364, Revision 4. hour = $3,060 per
inspection cycle.
HFEC inspections per Service Bulletin 128 work-hours x $85 per 0 $10,880 per inspection cycle....... $707,200 per inspection cycle.
A3364, Revision 4. hour = $10,880 per
inspection cycle.
Inspections per Service Bulletin 20 work-hours x $85 per 0 $1,700 per inspection cycle........ $110,500 per inspection cycle.
A3365, Revision 3. hour = $1,700 per
inspection cycle.
Detailed inspections per Service 12 work-hours x $85 per 0 $1,020 per inspection cycle........ $66,300 per inspection cycle.
Bulletin A3514, Revision 1. hour = $1,020 per
inspection cycle.
HFEC inspections per Service Bulletin 32 work-hours x $85 per 0 $2,720 per inspection cycle........ $176,800 per inspection cycle.
A3514, Revision 1. hour = $2,720 per
inspection cycle.
--------------------------------------------------------------------------------------------------------------------------------------------------------
We estimate that any necessary replacement of affected fittings
would take about 96 work-hours for a cost of $8,160 per fitting. We
have received no definitive data on the parts costs of the affected
fittings. We have no way of determining the number of aircraft that
might need this replacement.
We have received no definitive data that would enable us to provide
cost estimates for the on-condition actions specified in this AD.
Authority for This Rulemaking
Title 49 of the United States Code specifies the FAA's authority to
issue rules on aviation safety. Subtitle I, section 106, describes the
authority of the FAA Administrator. Subtitle VII: Aviation Programs,
describes in more detail the scope of the Agency's authority.
We are issuing this rulemaking under the authority described in
Subtitle VII, Part A, Subpart III, Section 44701: ``General
requirements.'' Under that section, Congress charges the FAA with
promoting safe flight of civil aircraft in air commerce by prescribing
regulations for practices, methods, and procedures the Administrator
finds necessary for safety in air commerce. This regulation is within
the scope of that authority because it addresses an unsafe condition
that is likely to exist or develop on products identified in this
rulemaking action.
This 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
This AD will not have federalism implications under Executive Order
13132. This AD will not have a substantial direct effect on the States,
on the relationship between the national government and the States, or
on the distribution of power and responsibilities among the various
levels of government.
For the reasons discussed above, I certify that this AD:
(1) Is not a ``significant regulatory action'' under Executive
Order 12866,
(2) Is not a ``significant rule'' under DOT Regulatory Policies and
Procedures (44 FR 11034, February 26, 1979),
(3) Will not affect intrastate aviation in Alaska, and
(4) Will not have a significant economic impact, positive or
negative, on a substantial number of small entities under the criteria
of the Regulatory Flexibility Act.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.
Adoption of the Amendment
Accordingly, under the authority delegated to me by the
Administrator, the FAA amends 14 CFR part 39 as follows:
PART 39--AIRWORTHINESS DIRECTIVES
0
1. The authority citation for part 39 continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
Sec. 39.13 [Amended]
0
2. The FAA amends Sec. 39.13 by adding the following new airworthiness
directive (AD):
2018-19-32 The Boeing Company: Amendment 39-19433; Docket No. FAA-
2018-0504; Product Identifier 2018-NM-046-AD.
(a) Effective Date
This AD is effective November 2, 2018.
(b) Affected ADs
This AD affects AD 82-24-03, Amendment 39-4496 (47 FR 51099,
November 12, 1982) (``AD 82-24-03'') and AD 2005-08-15, Amendment
39-14067 (70 FR 21136, April 25, 2005) (``AD 2005-08-15'').
(c) Applicability
This AD applies to all The Boeing Company Model 707-100 Long
Body, -200, -100B Long Body, and -100B Short Body series airplanes;
Model 707-300, -300B, -300C, and -400 series airplanes; and Model
720 and 720B series airplanes; certificated in any category.
(d) Subject
Air Transport Association (ATA) of America Code 54, Nacelles/
pylons.
(e) Unsafe Condition
This AD was prompted by a report indicating that a fracture of
the midspar fitting resulted in the separation of the
[[Page 48929]]
inboard strut and engine from the airplane, and a determination that
existing inspections for other nacelle strut fittings are not
sufficient for timely detection of cracking. We are issuing this AD
to address cracks, which if not detected and corrected, could grow
beyond a critical length, allowing the strut fitting to fail and
reducing the structural integrity of the nacelle. This, in
combination with damage to adjacent attachment structure, could
result in the loss of an engine from the airplane.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(g) Repetitive Detailed Inspections of the Front Spar Fittings at
Nacelle Struts Numbers 1, 2, 3, and 4
Prior to the accumulation of 3,500 total flight hours; within
700 flight hours after the most recent inspection specified in
Boeing 707 Alert Service Bulletin A3514, dated July 29, 2004, was
done; or within three months after the effective date of this AD;
whichever occurs later: Do a detailed inspection for cracking of the
front spar fittings at nacelle struts numbers 1, 2, 3, and 4, in
accordance with the Accomplishment Instructions of Boeing 707 Alert
Service Bulletin A3514, Revision 1, dated November 9, 2016. If any
cracking is found, before further flight, replace the affected
fitting, in accordance with the Accomplishment Instructions of
Boeing 707 Alert Service Bulletin A3514, Revision 1, dated November
9, 2016. Repeat the inspections thereafter at intervals not to
exceed 700 flight hours.
(h) Repetitive Surface High Frequency Eddy Current (HFEC) Inspections
of the Aft Lugs on the Front Spar Fittings at Nacelle Struts Numbers 1,
2, 3, and 4
Within 1,500 flight cycles or 48 months after the most recent
detailed inspection required by paragraph (g) of this AD was done,
whichever occurs first, do a surface HFEC inspection for cracking of
the aft lugs on the front spar fittings at nacelle struts numbers 1,
2, 3, and 4, and do all applicable corrective actions, in accordance
with the Accomplishment Instructions of Boeing 707 Alert Service
Bulletin A3514, Revision 1, dated November 9, 2016, except as
required by paragraph (l)(4) of this AD. Do all applicable
corrective actions before further flight. Repeat the inspection
thereafter at intervals not to exceed 1,500 flight cycles or 48
months, whichever occurs first.
(i) Repetitive Inspections of the Overwing Support Fitting at Nacelle
Struts Numbers 1, 2, 3, and 4
At the times specified in paragraph 1.E., ``Compliance,'' of
Boeing 707 Alert Service Bulletin A3365, Revision 3, dated March 9,
2017, except as required by paragraph (l)(1) of this AD: Do the
inspections specified in paragraphs (i)(1) through (i)(3) of this AD
and do all applicable related investigative and corrective actions,
in accordance with the Accomplishment Instructions of Boeing 707
Alert Service Bulletin A3365, Revision 3, dated March 9, 2017,
except as required by paragraph (l)(3) of this AD. Do all applicable
related investigative and corrective actions before further flight.
Repeat the inspections thereafter at the applicable time specified
in paragraph 1.E., ``Compliance,'' of Boeing 707 Alert Service
Bulletin A3365, Revision 3, dated March 9, 2017.
(1) Do a detailed inspection for any crack at all five holes in
the overwing support fitting, and at the flange radii.
(2) Do the inspection specified in paragraph (i)(2)(i) or
(i)(2)(ii) of this AD.
(i) Do a surface HFEC inspection for any crack in the overwing
support fitting around the hole immediately forward of the spar
chord, with the bolt in place, and at the flange radii.
(ii) Do an open hole HFEC inspection for any crack in the
overwing support fitting at the hole immediately forward of the spar
chord.
(3) Do the inspection specified in paragraph (i)(3)(i) or
(i)(3)(ii) of this AD.
(i) Do an ultrasonic inspection for any crack in the overwing
support fitting around the four holes common to the fitting and the
spar chord, with the bolts in place.
(ii) Do a surface HFEC inspection for any crack in the overwing
support fitting around the four holes common to the fitting and the
spar chord, with the bolts in place.
(j) Inspections of the Nacelle Strut Diagonal Braces and Associated
Fittings
For airplanes with nacelle strut diagonal braces and associated
fittings which have accumulated 7,500 flight cycles or more: At the
applicable times specified in paragraph 1.E., ``Compliance'' of
Boeing 707 Alert Service Bulletin A3364, Revision 4, dated February
21, 2017, except as required by paragraph (l)(2) of this AD, do the
inspections specified in paragraphs (j)(1) through (j)(3) of this
AD. Repeat the inspections thereafter at the applicable intervals
specified in tables 1, 2, 3, and 4 of paragraph 1.E.,
``Compliance,'' of Boeing 707 Alert Service Bulletin A3364, Revision
4, dated February 21, 2017. If any crack is found during any
inspection required by this paragraph, before further flight, do all
applicable corrective actions, in accordance with the Accomplishment
Instructions of Boeing 707 Alert Service Bulletin A3364, Revision 4,
dated February 21, 2017, except as required by paragraph (l)(3) of
this AD.
(1) Do a detailed inspection of the nacelle strut diagonal brace
end fittings, diagonal brace tube, forward mating fitting, and aft
mating fitting for any crack.
(2) Do HFEC inspections of the nacelle strut diagonal brace end
fittings, forward mating fitting, and aft mating fitting for any
crack. As an alternative for the aft mating fitting, do a dye
penetrant inspection of vertical webs on aft mating fitting for any
crack.
(3) Do an HFEC inspection of the diagonal brace tube for any
crack.
(k) Replacement
For Group 3, 4, and 6 airplanes as identified in Boeing 707
Alert Service Bulletin A3364, Revision 4, dated February 21, 2017,
on which the outboard diagonal brace end fitting (forward or aft)
attach holes have been oversized as specified in Boeing 707 Alert
Service Bulletin A3364, Revision 3, dated May 29, 1981: Within 1,000
flight cycles after the effective date of this AD, replace the
diagonal brace assembly, in accordance with Figure 3 of Boeing 707
Alert Service Bulletin A3364, Revision 4, dated February 21, 2017.
(l) Exceptions to Service Information Specifications
(1) For purposes of determining compliance with the requirements
of this AD: Where Boeing 707 Alert Service Bulletin A3365, Revision
3, dated March 9, 2017, uses the phrase ``the Revision 3 date of
this service bulletin,'' this AD requires using ``the effective date
of this AD.''
(2) For purposes of determining compliance with the requirements
of this AD: Where Boeing 707 Alert Service Bulletin A3364, Revision
4, dated February 21, 2017, uses the phrase ``the Revision 4 date of
this service bulletin,'' this AD requires using ``the effective date
of this AD.''
(3) Where Boeing 707 Alert Service Bulletin A3364, Revision 4,
dated February 21, 2017; and Boeing 707 Alert Service Bulletin
A3365, Revision 3, dated March 9, 2017; specify contacting Boeing:
This AD requires repair using a method approved in accordance with
the procedures specified in paragraph (o) of this AD.
(4) Where Boeing 707 Alert Service Bulletin A3514, Revision 1,
dated November 9, 2016, specifies contacting Boeing for replacement
instructions: This AD requires replacement using a method approved
in accordance with the procedures specified in paragraph (o) of this
AD.
(m) Terminating Action for Other ADs
(1) Accomplishing the initial inspections required by paragraph
(j) of this AD terminates all requirements of AD 82-24-03.
(2) Accomplishing the initial inspections required by paragraph
(g) of this AD, terminates all requirements of AD 2005-08-15.
(n) Parts Installation Prohibition
As of the effective date of this AD, no person may install, on
any airplane, a front spar fitting having a part number other than
the part numbers specified in paragraph 2.C.2. of Boeing 707 Alert
Service Bulletin A3514, Revision 1, dated November 9, 2016.
(o) Alternative Methods of Compliance (AMOCs)
(1) The Manager, Los Angeles 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(s) identified in paragraph (p)(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.
[[Page 48930]]
(3) An AMOC that provides an acceptable level of safety may be
used for any repair, modification, replacement, or alteration
required by this AD if it is approved by the Boeing Commercial
Airplanes Organization Designation Authorization (ODA) that has been
authorized by the Manager, Los Angeles ACO Branch, FAA, to make
those findings. To be approved, the repair method, modification
deviation, replacement deviation, or alteration deviation must meet
the certification basis of the airplane, and the approval must
specifically refer to this AD.
(p) Related Information
(1) For more information about this AD, contact Jeffrey Chang,
Aerospace Engineer, Propulsion Section, FAA, Los Angeles ACO Branch,
3960 Paramount Boulevard, Lakewood, CA 90712-4137; phone: 562-627-
5263; fax: 562-627-5210; email: [email protected]; or George
Garrido, Aerospace Engineer, Airframe Section, FAA, Los Angeles ACO
Branch, 3960 Paramount Boulevard, Lakewood, CA 90712-4137; phone:
562-627-5232; fax: 562-627-5210; email [email protected].
(2) Service information identified in this AD that is not
incorporated by reference is available at the addresses specified in
paragraphs (q)(3) and (q)(4) of this AD.
(q) 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 707 Alert Service Bulletin A3364, Revision 4, dated
February 21, 2017.
(ii) Boeing 707 Alert Service Bulletin A3365, Revision 3, dated
March 9, 2017.
(iii) Boeing 707 Alert Service Bulletin A3514, Revision 1, dated
November 9, 2016.
(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, 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.
(5) You may view this service information that is incorporated
by reference at the National Archives and Records Administration
(NARA). For information on the availability of this material at
NARA, call 202-741-6030, or go to: https://www.archives.gov/federal-register/cfr/ibr-locations.html.
Issued in Des Moines, Washington, on September 17, 2018.
John P. Piccola,
Acting Director, System Oversight Division, Aircraft Certification
Service.
[FR Doc. 2018-20918 Filed 9-27-18; 8:45 am]
BILLING CODE 4910-13-P
