Airworthiness Directives; The Boeing Company Airplanes, 74052-74056 [2015-30120]
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Federal Register / Vol. 80, No. 228 / Friday, November 27, 2015 / Proposed Rules
(u) Alternative Methods of Compliance
(AMOCs)
DEPARTMENT OF TRANSPORTATION
(1) The Manager, Los Angeles Aircraft
Certification Office (ACO), 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 ACO, send it to the
attention of the person identified in
paragraph (v)(1) of this AD. Information may
be emailed to: 9-ANM-LAACO-AMOCRequests@faa.gov.
(2) Before using any approved AMOC,
notify your appropriate principal inspector,
or lacking a principal inspector, the manager
of the local flight standards district office/
certificate holding district office.
(3) An AMOC that provides an acceptable
level of safety may be used for any repair,
modification, or alteration required by this
AD if it is approved by the Boeing
Commercial Airplanes Organization
Designation Authorization (ODA) that has
been authorized by the Manager, Seattle
ACO, to make those findings. To be
approved, the repair method, modification
deviation, or alteration deviation must meet
the certification basis of the airplane and the
approval must specifically refer to this AD.
(4) AMOCs approved for AD 2009–02–06,
Amendment 39–15796 (74 FR 10469, March
11, 2009); AD 2009–02–06 R1, Amendment
39–16015 (74 FR 45979, September 6, 2009);
and AD 2011–23–05, Amendment 39–16856
(76 FR 67343, November 1, 2011); are
approved as AMOCs for the corresponding
provisions of this AD.
Federal Aviation Administration
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(v) Related Information
(1) For more information about this AD,
contact Wayne Lockett, Aerospace Engineer,
Airframe Branch, ANM–120S, Seattle
Aircraft Certification Office (ACO), FAA,
1601 Lind Avenue SW., Renton, Washington
98057–3356; phone: 425–917–6447; fax: 425–
917–6590; email: wayne.lockett@faa.gov.
(2) For service information identified in
this AD, contact Boeing Commercial
Airplanes, Attention: Data & Services
Management, P. O. Box 3707, MC 2H–65,
Seattle, WA 98124–2207; telephone 206–
544–5000, extension 1; fax 206–766–5680;
Internet https://www.myboeingfleet.com. You
may view this referenced service information
at the FAA, 1601 Lind Avenue SW., Renton,
Washington. For information on the
availability of this material at the FAA, call
425–227–1221.
Issued in Renton, Washington, on
November 17, 2015.
Jeffrey E. Duven,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. 2015–30008 Filed 11–25–15; 8:45 am]
BILLING CODE 4910–13–P
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14 CFR Part 39
[Docket No. FAA–2015–5816; Directorate
Identifier 2015–NM–029–AD]
RIN 2120–AA64
Airworthiness Directives; The Boeing
Company Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
We propose to supersede
Airworthiness Directive (AD) 2006–10–
16, which applies to all The Boeing
Company Model 747–100, 747–100B,
747–100B SUD, 747–200B, 747–200C,
747–200F, 747–300, 747–400, 747–
400D, 747–400F, 747SR, and 747SP
series airplanes. AD 2006–10–16
requires, for certain airplanes, repetitive
inspections for cracking of the outboard
and center sections of the horizontal
stabilizer, and repair if necessary. For
certain other airplanes, AD 2006–10–16
requires a detailed inspection to
determine the type of fasteners, and
related investigative actions and repair
if necessary. Since we issued AD 2006–
10–16, additional cracking was found in
the splice plates, hinge fittings, terminal
fittings, the upper skin of the outboard
and center sections, and the rear spar
webs before reaching the inspection
interval specified in AD 2006–10–16.
Cracked and fractured Maraging steel
fasteners were also found. This
proposed AD would reduce the
compliance time for certain inspections
and would add repetitive inspections
for cracking of the splice plates, hinge
fittings, terminal fittings, the upper skin
of the outboard and center sections, and
the rear spar webs in Zone B. This
proposed AD would also add an
inspection to determine whether
fasteners are magnetic in Zone C,
repetitive ultrasonic inspections for
cracking and fractures of affected
fasteners, and related investigative and
corrective actions if necessary. This
proposed AD would also add an
optional modification, which would
terminate certain repetitive inspections,
and would add post-modification
inspections and corrective action if
necessary. We are proposing this AD to
detect and correct this cracking, which
could lead to reduced structural
capability of the outboard and center
sections of the horizontal stabilizer and
could result in loss of control of the
airplane.
SUMMARY:
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We must receive comments on
this proposed AD by January 11, 2016.
ADDRESSES: You may send comments,
using the procedures found in 14 CFR
11.43 and 11.45, by any of the following
methods:
• Federal eRulemaking Portal: Go to
https://www.regulations.gov. Follow the
instructions for submitting comments.
• Fax: 202–493–2251.
• Mail: U.S. Department of
Transportation, Docket Operations, M–
30, West Building Ground Floor, Room
W12–140, 1200 New Jersey Avenue SE.,
Washington, DC 20590.
• Hand Delivery: Deliver to Mail
address above between 9 a.m. and 5
p.m., Monday through Friday, except
Federal holidays.
For service information identified in
this proposed AD, contact Boeing
Commercial Airplanes, Attention: Data
& Services Management, P. O. Box 3707,
MC 2H–65, Seattle, WA 98124–2207;
telephone: 206–544–5000, extension 1;
fax: 206–766–5680; Internet https://
www.myboeingfleet.com. You may view
this referenced service information at
the FAA, Transport Airplane
Directorate, 1601 Lind Avenue SW.,
Renton, WA. For information on the
availability of this material at the FAA,
call 425–227–1221. It is also available
on the Internet at https://
www.regulations.gov by searching for
and locating Docket No. FAA–2015–
5816.
DATES:
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–2015–
5816; or in person at the Docket
Management Facility between 9 a.m.
and 5 p.m., Monday through Friday,
except Federal holidays. The AD docket
contains this proposed AD, the
regulatory evaluation, any comments
received, and other information. The
street address for the Docket Office
(phone: 800–647–5527) is in the
ADDRESSES section. Comments will be
available in the AD docket shortly after
receipt.
FOR FURTHER INFORMATION CONTACT:
Nathan Weigand, Aerospace Engineer,
Airframe Branch, ANM–120S, FAA,
Seattle Aircraft Certification Office,
1601 Lind Avenue SW., Renton, WA
98057–3356; phone: 425–917–6428; fax:
425–917–6590; email:
nathan.p.weigand@faa.gov.
SUPPLEMENTARY INFORMATION:
Comments Invited
We invite you to send any written
relevant data, views, or arguments about
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this proposed AD. Send your comments
to an address listed under the
ADDRESSES section. Include ‘‘Docket No.
FAA–2015–5816; Directorate Identifier
2015–NM–029–AD’’ at the beginning of
your comments. We specifically invite
comments on the overall regulatory,
economic, environmental, and energy
aspects of this proposed AD. We will
consider all comments received by the
closing date and may amend this
proposed AD because of those
comments.
We will post all comments we
receive, without change, to https://
www.regulations.gov, including any
personal information you provide. We
will also post a report summarizing each
substantive verbal contact we receive
about this proposed AD.
Discussion
On May 8, 2006, we issued AD 2006–
10–16, Amendment 39–14600 (71 FR
28570, May 17, 2006), for all The Boeing
Company Model 747–100, 747–100B,
747–100B SUD, 747–200B, 747–200C,
747–200F, 747–300, 747–400, 747–
400D, 747–400F, 747SR, and 747SP
series airplanes. AD 2006–10–16
requires, for certain airplanes, repetitive
inspections for cracking of the outboard
and center sections of the horizontal
stabilizer, and repair if necessary. For
certain other airplanes, AD 2006–10–16
requires a detailed inspection to
determine the type of fasteners, related
investigative actions, and repair if
necessary. AD 2006–10–16 resulted
from reports of cracking in the outboard
and center section of the aft upper skin
of the horizontal stabilizer, the rear spar
chord, rear spar web, terminal fittings,
and splice plates; and a report of
fractured and cracked steel fasteners.
We issued AD 2006–10–16 to detect and
correct this cracking, which could lead
to reduced structural capability of the
outboard and center sections of the
horizontal stabilizer and could result in
loss of control of the airplane.
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Actions Since AD 2006–10–16,
Amendment 39–14600 (71 FR 28570,
May 17, 2006), Was Issued
Since we issued AD 2006–10–16,
Amendment 39–14600 (71 FR 28570,
May 17, 2006), additional cracking was
found in the splice plates, hinge fittings,
terminal fittings, the upper skin of the
outboard and center sections, and the
rear spar webs before reaching the
inspection interval specified in AD
2006–10–16. Cracked and fractured
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Maraging steel fasteners were also
found.
Related Service Information Under 1
CFR Part 51
We reviewed Boeing Service Bulletin
747–55A2050, Revision 2, dated January
23, 2015. The service information
describes procedures for accomplishing
Zone A, Zone B, and Zone C inspections
for cracking of the upper skin and upper
rear spar chord of the outboard and
center sections of the horizontal
stabilizer, and related investigative and
corrective actions if necessary. The
service information also describes
procedures for a magnetic inspection to
determine the type of fasteners,
ultrasonic inspections for cracking and
fractures of affected fasteners, and
related investigative actions and
corrective actions if necessary. The
service information also describes
procedures for an optional modification,
which would end certain repetitive
inspections, and procedures for postmodification inspections and corrective
action if necessary. 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 of this NPRM.
FAA’s Determination
We are proposing this AD because we
evaluated all the relevant information
and determined the unsafe condition
described previously is likely to exist or
develop in other products of the same
type design.
Proposed AD Requirements
Although this proposed AD does not
explicitly restate the requirements of AD
2006–10–16, Amendment 39–14600 (71
FR 28570, May 17, 2006), this proposed
AD would retain all of the requirements.
Those requirements are referenced in
the service information identified
previously, which, in turn, is referenced
in paragraph (g) of this proposed AD.
This proposed AD would reduce the
compliance time for certain inspections
and add new repetitive inspections for
cracking of the splice plates, hinge
fittings, terminal fittings, the upper skin
of the outboard and center sections, and
the rear spar webs in Zone B. This
proposed AD would also add an
inspection to determine whether
fasteners are magnetic in Zone C (made
of H–11 steel), repetitive ultrasonic
inspections for cracking and fractures of
affected fasteners, and related
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investigative and corrective actions if
necessary. This proposed AD would
also add an optional modification,
which would end certain repetitive
inspections, and procedures for postmodification inspections and corrective
action if necessary. This proposed AD
also adds optional open-hole NDT
inspections (high frequency eddy
current inspections) for certain
airplanes, for Zone B inspections. This
proposed AD would also require
accomplishing the actions specified in
the service information described
previously, except as discussed under
‘‘Difference Between this Proposed AD
and the Service Bulletin.’’ For
information on the procedures and
compliance times, see this service
information at https://
www.regulations.gov by searching for
and locating Docket No. FAA–2015–
5816.
The phrase ‘‘related investigative
actions’’ is used in this proposed AD.
‘‘Related investigative actions’’ are
follow-on actions that (1) are related to
the primary action, and (2) further
investigate the nature of any condition
found. Related investigative actions in
an AD could include, for example,
inspections.
The phrase ‘‘corrective actions’’ is
used in this proposed AD. ‘‘Corrective
actions’’ are actions that correct or
address any condition found. Corrective
actions in an AD could include, for
example, repairs.
Difference Between This Proposed AD
and the Service Bulletin
Although Boeing Service Bulletin
747–55A2050, Revision 2, dated January
23, 2015, specifies that operators may
contact the manufacturer for disposition
of certain repair conditions, this
proposed AD would require repairing
those conditions in one of the following
ways:
• In accordance with a method that
we approve; or
• Using data that meet the
certification basis of the airplane, and
that have been approved by the Boeing
Commercial Airplanes Organization
Designation Authorization (ODA) whom
we have authorized to make those
findings.
Costs of Compliance
We estimate that this proposed AD
affects 116 airplanes of U.S. registry.
We estimate the following costs to
comply with this proposed AD:
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ESTIMATED COSTS—REQUIRED ACTIONS
Action
Labor cost
Zone A Inspections (required by AD 2006–
10–16, Amendment 39–14600).
Zone B Open-hole NDT Inspection (required
by AD 2006–10–16, Amendment 39–14600
for Groups 3, 4, and 5 airplanes; and for
Groups 1, 2, and 3 airplanes, if done).
Zone C Maraging or H–11 Steel Fastener Inspection (required by AD 2006–10–16,
Amendment 39–14600 for Groups 1, 2,
and 3 airplanes).
New Zone B proposed inspections ................
New Zone C proposed inspection ..................
Cost per
product
Parts cost
Cost on U.S. operators
8 work-hours × $85 per hour
= $680.
30 work-hours × 85 per hour
= 2,550.
$0
$680
Up to $78,880.
0
2,550
Up to $295,800.
8 work-hours × 85 per hour =
680.
0
680
248 work-hours × 85 per hour
= 21,080.
26 work-hours × 85 per hour
= 2,210.
0
21,080
0
2,210
Up to $78,880.
$2,445,280.
$256,360.
ESTIMATED COSTS—OPTIONAL ACTIONS
Action
Labor cost
Parts cost
Open-hole NDT inspections (high
frequency eddy current inspections.
Zone B Modification .......................
Up to 298 work-hours × $85 per
hour = up to $25,330.
$$0 ................................................
Up to $25,330.
Up to 313 work-hours × $85 per
hour = up to $26,605.
Up to 298 work-hours × $85 per
hour = up to $25,330.
Up to $3,486 .................................
Up to $30,091.
$0 ..................................................
Up to $25,330.
Post-Modification Inspections ........
We have received no definitive data
that would enable us to provide a cost
estimate for the on-condition actions
specified in this proposed AD.
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Authority for This Rulemaking
Title 49 of the United States Code
specifies the FAA’s authority to issue
rules on aviation safety. Subtitle I,
Section 106, describes the authority of
the FAA Administrator. Subtitle VII,
Aviation Programs, describes in more
detail the scope of the Agency’s
authority.
We are issuing this rulemaking under
the authority described in Subtitle VII,
Part A, Subpart III, Section 44701,
‘‘General requirements.’’ Under that
section, Congress charges the FAA with
promoting safe flight of civil aircraft in
air commerce by prescribing regulations
for practices, methods, and procedures
the Administrator finds necessary for
safety in air commerce. This regulation
is within the scope of that authority
because it addresses an unsafe condition
that is likely to exist or develop on
products identified in this rulemaking
action.
Regulatory Findings
We have determined that this
proposed AD would not have federalism
implications under Executive Order
13132. This proposed AD would not
have a substantial direct effect on the
States, on the relationship between the
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national Government and the States, or
on the distribution of power and
responsibilities among the various
levels of government.
For the reasons discussed above, I
certify that the proposed regulation:
(1) Is not a ‘‘significant regulatory
action’’ under Executive Order 12866,
(2) Is not a ‘‘significant rule’’ under
the DOT Regulatory Policies and
Procedures (44 FR 11034, February 26,
1979),
(3) Will not affect intrastate aviation
in Alaska, and
(4) Will not have a significant
economic impact, positive or negative,
on a substantial number of small entities
under the criteria of the Regulatory
Flexibility Act.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation
safety, Incorporation by reference,
Safety.
The Proposed Amendment
Accordingly, under the authority
delegated to me by the Administrator,
the FAA proposes to amend 14 CFR part
39 as follows:
PART 39—AIRWORTHINESS
DIRECTIVES
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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Cost per product
§ 39.13
[Amended]
2. The FAA amends § 39.13 by
removing Airworthiness Directive AD
2006–10–16, Amendment 39–14600 (71
FR 28570, May 17, 2006), and adding
the following new AD:
■
The Boeing Company: Docket No. FAA–
2015–5816; Directorate Identifier 2015–
NM–029–AD.
(a) Comments Due Date
The FAA must receive comments on this
AD action by January 11, 2016.
(b) Affected ADs
This AD replaces AD 2006–10–16,
Amendment 39–14600 (71 FR 28570, May 17,
2006).
(c) Applicability
This AD applies to all The Boeing
Company Model 747–100, 747–100B, 747–
100B SUD, 747–200B, 747–200C, 747–200F,
747–300, 747–400, 747–400D, 747–400F,
747SR, and 747SP series airplanes;
certificated in any category.
(d) Subject
Air Transport Association (ATA) of
America Code 55, Stabilizers.
(e) Unsafe Condition
This AD was prompted by reports of
cracking found in the splice plates, hinge
fittings, terminal fittings, the upper skin of
the outboard and center sections, and the rear
spar webs before reaching the inspection
interval specified in AD 2006–10–16.
Cracked and fractured Maraging steel
fasteners were also found. We are issuing this
AD to detect and correct this cracking, which
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could lead to reduced structural capability of
the outboard and center sections of the
horizontal stabilizer and could result in loss
of control of the airplane.
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(f) Compliance
Comply with this AD within the
compliance times specified, unless already
done.
(g) Repetitive Inspections/Investigative and
Corrective Actions
At the applicable time specified in
paragraph 1.E., ‘‘Compliance,’’ of Boeing
Service Bulletin 747–55A2050, Revision 2,
dated January 23, 2015, except as required by
paragraphs (h)(1) and (h)(2) of this AD: Do
the applicable actions specified in
paragraphs (g)(1), (g)(2), (g)(3), and (g)(4) of
this AD, and all applicable related
investigative and corrective actions, in
accordance with the applicable part of the
Accomplishment Instructions of Boeing
Service Bulletin 747–55A2050, Revision 2,
dated January 23, 2015, except as required by
paragraph (h)(3) of this AD. Do all applicable
related investigative and corrective actions
before further flight. Repeat the applicable
inspections specified in paragraphs (g)(1),
(g)(2), (g)(3), and (g)(4) of this AD at the
applicable times specified in paragraph 1.E.,
‘‘Compliance,’’ of Boeing Service Bulletin
747–55A2050, Revision 2, dated January 23,
2015.
(1) For Group 1 through 3 airplanes
identified in Boeing Service Bulletin 747–
55A2050, Revision 2, dated January 23, 2015:
Do non-destructive test (NDT) inspections
(ultrasonic, high frequency eddy current, and
low frequency eddy current inspections) or
open-hole NDT inspections (high frequency
eddy current inspections), of Zone B for
cracking in accordance with Part 3 or Part 4
of the Accomplishment Instructions of
Boeing Service Bulletin 747–55A2050,
Revision 2, dated January 23, 2015, as
applicable.
(2) For Group 4 through 6 airplanes
identified in Boeing Service Bulletin 747–
55A2050, Revision 2, dated January 23, 2015:
Do open-hole NDT inspections (high
frequency eddy current inspections), of Zone
B for cracking in accordance with Part 4 of
the Accomplishment Instructions of Boeing
Service Bulletin 747–55A2050, Revision 2,
dated January 23, 2015.
(3) For Group 7 through 9 airplanes
identified in Boeing Service Bulletin 747–
55A2050, Revision 2, dated January 23, 2015:
Do inspections of Zone A (detailed or high
frequency eddy current inspections) and
Zone B (high frequency eddy current
inspections) for cracking, in accordance with
Part 1, Part 2, or Part 4 of the
Accomplishment Instructions of Boeing
Service Bulletin 747–55A2050, Revision 2,
dated January 23, 2015, as applicable.
(4) For Group 1 through 3 airplanes
identified in Boeing Service Bulletin 747–
55A2050, Revision 2, dated January 23, 2015:
Do an inspection of Zone C Maraging or H–
11 steel fasteners to determine whether
fasteners are magnetic, in accordance with
Part 6 of the Accomplishment Instructions of
Boeing Service Bulletin 747–55A2050,
Revision 2, dated January 23, 2015.
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(h) Exceptions to Service Bulletin
Specifications
(1) Where Boeing Service Bulletin 747–
55A2050, Revision 2, dated January 23, 2015,
specifies a compliance time ‘‘after the
Revision 2 date of this service bulletin,’’ this
AD requires compliance within the specified
compliance time after the effective date of
this AD.
(2) The Condition column of Table 1 of
paragraph 1.E., ‘‘Compliance,’’ of Boeing
Service Bulletin 747–55A2050, Revision 2,
dated January 23, 2015, refers to ‘‘airplanes
with certain total flight cycles and total flight
hours.’’ This AD, however, applies to the
airplanes with the specified total flight cycles
and total flight hours as of the effective date
of this AD.
(3) Where Boeing Service Bulletin 747–
55A2050, Revision 2, dated January 23, 2015,
specifies to contact Boeing for repair
instructions: Before further flight, repair
using a method approved in accordance with
the procedures specified in paragraph (l) of
this AD.
(i) Optional Terminating Action
(1) For Group 1 through 3 airplanes
identified in Boeing Service Bulletin 747–
55A2050, Revision 2, dated January 23, 2015:
Accomplishing the Zone B modification,
including all applicable related investigative
and corrective actions, specified in Part 7 of
the Accomplishment Instructions of Boeing
Service Bulletin 747–55A2050, Revision 2,
dated January 23, 2015, except as required by
paragraph (h)(3) of this AD, terminates the
repetitive inspections specified in paragraphs
(i)(1)(i) and (i)(1)(ii) of this AD for the
modified area only.
(i) Inspections required by paragraph (g)(1)
of this AD for Zone B, as specified in Part
3 and Part 4 of the Accomplishment
Instructions of Boeing Service Bulletin 747–
55A2050, Revision 2, dated January 23, 2015.
(ii) Inspections required by paragraph (g)(4)
of this AD for Zone C, as specified in Part
5 and Part 6 of the Accomplishment
Instructions of Boeing Service Bulletin 747–
55A2050, Revision 2, dated January 23, 2015.
(2) For Group 1 through 3 airplanes
identified in Boeing Service Bulletin 747–
55A2050, Revision 2, dated January 23, 2015:
Accomplishing the Zone B open hole NDT
inspection, repairing any cracking as
applicable, and replacing fasteners as
specified in Part 4 of the Accomplishment
Instructions of Boeing Service Bulletin 747–
55A2050, Revision 2, dated January 23, 2015,
terminates the repetitive ultrasonic
inspections required by paragraph (g)(4) of
this AD for Zone C, as specified in Part 6 of
the Accomplishment Instructions of Boeing
Service Bulletin 747–55A2050, Revision 2,
dated January 23, 2015, for the inspected area
only.
(3) For Group 4 through 9 airplanes
identified in Boeing Service Bulletin 747–
55A2050, Revision 2, dated January 23, 2015:
Accomplishing the Zone B modification,
including all applicable related investigative
and corrective actions, specified in Part 7 of
the Accomplishment Instructions of Boeing
Service Bulletin 747–55A2050, Revision 2,
dated January 23, 2015, except as required by
paragraph (h)(3) of this AD, terminates the
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74055
repetitive inspections required by paragraph
(g)(2) or (g)(3) of this AD, as applicable, only
for Zone B, as specified in Part 4 of the
Accomplishment Instructions of Boeing
Service Bulletin 747–55A2050, Revision 2,
dated January 23, 2015, for the modified area
only.
(j) Repetitive Post-Modification Inspections
and Corrective Actions
At the applicable time specified in
paragraph 1.E., ‘‘Compliance,’’ of Boeing
Service Bulletin 747–55A2050, Revision 2,
dated January 23, 2015: Do the applicable
inspections specified in paragraphs (j)(1) and
(j)(2) of this AD and all applicable corrective
actions, in accordance with Part 8 of the
Accomplishment Instructions of Boeing
Service Bulletin 747–55A2050, Revision 2,
dated January 23, 2015, except as required by
paragraph (h)(3) of this AD. Do all applicable
corrective actions before further flight.
Repeat the applicable inspections at the
applicable times specified in paragraph 1.E.,
‘‘Compliance,’’ of Boeing Service Bulletin
747–55A2050, Revision 2, dated January 23,
2015.
(1) For Group 1 through 3 airplanes
identified in Boeing Service Bulletin 747–
55A2050, Revision 2, dated January 23, 2015
on which the Zone B modification specified
in paragraph (i)(1) of this AD is done: Do
non-destructive test (NDT) inspections
(ultrasonic, high frequency eddy current, and
low frequency eddy current inspections) or
open-hole NDT inspections (high frequency
eddy current inspections) of Zone B for
cracking.
(2) For Group 4 through 9 airplanes
identified in Boeing Service Bulletin 747–
55A2050, Revision 2, dated January 23, 2015
on which the Zone B modification specified
in paragraph (i)(3) of this AD is done: Do
open-hole NDT inspections (high frequency
eddy current inspections) of Zone B for
cracking.
(k) Parts Installation Prohibition
As of the effective date of this AD, no
person may install any Maraging or H–11
steel fasteners in the locations specified in
this AD. Where Boeing Service Bulletin 747–
55A2050, Revision 2, dated January 23, 2015,
specifies to install H–11 bolts (kept
fasteners), this AD requires installation of
Inconel bolts.
(l) Alternative Methods of Compliance
(AMOCs)
(1) The Manager, Seattle Aircraft
Certification Office (ACO), 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 ACO, send it to the
attention of the person identified in
paragraph (m)(1) of this AD. Information may
be emailed to: 9-ANM-Seattle-ACO-AMOCRequests@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. 80, No. 228 / Friday, November 27, 2015 / Proposed Rules
(3) An AMOC that provides an acceptable
level of safety may be used for any repair
required by this AD if it is approved by the
Boeing Commercial Airplanes Organization
Designation Authorization (ODA) that has
been authorized by the Manager, Seattle
ACO, to make those findings. For a repair
method to be approved, the repair must meet
the certification basis of the airplane, and the
approval must specifically refer to this AD.
(4) AMOCs approved for AD 2006–10–16,
Amendment 39–14600 (71 FR 28570, May 17,
2006), are approved as AMOCs for the
corresponding provisions of paragraph (g) of
this AD, except for approved AMOCs that
allow installation of Maraging or H–11 steel
fasteners.
(m) Related Information
(1) For more information about this AD,
contact Nathan Weigand, Aerospace
Engineer, Airframe Branch, ANM–120S,
FAA, Seattle ACO, 1601 Lind Avenue SW.,
Renton, WA 98057–3356; phone: 425–917–
6428; fax: 425–917–6590; email:
nathan.p.weigand@faa.gov.
(2) For service information identified in
this AD, contact Boeing Commercial
Airplanes, Attention: Data & Services
Management, P. O. Box 3707, MC 2H–65,
Seattle, WA 98124–2207; telephone: 206–
544–5000, extension 1; fax: 206–766–5680;
Internet https://www.myboeingfleet.com. You
may view this referenced service information
at the FAA, Transport Airplane Directorate,
1601 Lind Avenue SW., Renton, WA. For
information on the availability of this
material at the FAA, call 425–227–1221.
Issued in Renton, Washington, on
November 19, 2015.
Michael Kaszycki,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. 2015–30120 Filed 11–25–15; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2015–5813; Directorate
Identifier 2014–NM–111–AD]
RIN 2120–AA64
Airworthiness Directives; Dassault
Aviation Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking
(NPRM).
mstockstill on DSK4VPTVN1PROD with PROPOSALS
AGENCY:
We propose to adopt a new
airworthiness directive (AD) for certain
Dassault Aviation Model FALCON 7X
airplanes. This proposed AD was
prompted by a fuel leak that occurred in
the baggage compartment during fuel
system pressurization. This proposed
AD would require opening the fuel
SUMMARY:
VerDate Sep<11>2014
16:45 Nov 25, 2015
Jkt 238001
boxes and restoring the sealing. We are
proposing this AD to detect and correct
failure of a connector or coupling on a
fuel line, which, in combination with a
leak in the corresponding enclosure
(i.e., fuel box), could result in a fire in
the baggage compartment and affect the
safe flight of the airplane.
DATES: We must receive comments on
this proposed AD by January 11, 2016.
ADDRESSES: You may send comments,
using the procedures found in 14 CFR
11.43 and 11.45, by any of the following
methods:
• Federal eRulemaking Portal: Go to
https://www.regulations.gov. Follow the
instructions for submitting comments.
• Fax: 202–493–2251.
• Mail: U.S. Department of
Transportation, Docket Operations, M–
30, West Building Ground Floor, Room
W12–140, 1200 New Jersey Avenue SE.,
Washington, DC 20590.
• Hand Delivery: U.S. Department of
Transportation, Docket Operations, M–
30, West Building Ground Floor, Room
W12–140, 1200 New Jersey Avenue SE.,
Washington, DC, between 9 a.m. and 5
p.m., Monday through Friday, except
Federal holidays.
For service information identified in
this proposed AD, contact Dassault
Falcon Jet, P.O. Box 2000, South
Hackensack, NJ 07606; telephone 201–
440–6700; Internet https://
www.dassaultfalcon.com. You may
view this referenced service information
at the FAA, Transport Airplane
Directorate, 1601 Lind Avenue SW.,
Renton, WA. For information on the
availability of this material at the FAA,
call 425–227–1221.
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–2015–
5813; or in person at the Docket
Management Facility between 9 a.m.
and 5 p.m., Monday through Friday,
except Federal holidays. The AD docket
contains this proposed AD, the
regulatory evaluation, any comments
received, and other information. The
street address for the Docket Operations
office (telephone 800–647–5527) is in
the ADDRESSES section. Comments will
be available in the AD docket shortly
after receipt.
FOR FURTHER INFORMATION CONTACT: Tom
Rodriguez, Aerospace Engineer,
International Branch, ANM–116,
Transport Airplane Directorate, FAA,
1601 Lind Avenue SW., Renton, WA
98057–3356; telephone (425) 227–1137;
fax (425) 227–1149.
SUPPLEMENTARY INFORMATION:
PO 00000
Frm 00053
Fmt 4702
Sfmt 4702
Comments Invited
We invite you to send any written
relevant data, views, or arguments about
this proposed AD. Send your comments
to an address listed under the
ADDRESSES section. Include ‘‘Docket No.
FAA–2015–5813; Directorate Identifier
2014–NM–111–AD’’ at the beginning of
your comments. We specifically invite
comments on the overall regulatory,
economic, environmental, and energy
aspects of this proposed AD. We will
consider all comments received by the
closing date and may amend this
proposed AD based on those comments.
We will post all comments we
receive, without change, to https://
www.regulations.gov, including any
personal information you provide. We
will also post a report summarizing each
substantive verbal contact we receive
about this proposed AD.
Discussion
The European Aviation Safety Agency
(EASA), which is the Technical Agent
for the Member States of the European
Union, has issued EASA Airworthiness
Directive 2014–0116, dated May 13,
2014 (referred to after this as the
Mandatory Continuing Airworthiness
Information, or ‘‘the MCAI’’), to correct
an unsafe condition for certain Dassault
Aviation Model FALCON 7X airplanes.
The MCAI states:
During the fuel system pressurization of a
production line Falcon 7X aeroplane, a fuel
leak occurred in the baggage compartment.
The technical investigations concluded that a
double failure of a connector (or coupling) on
a fuel line, in combination with a defective
fuel tightness of the corresponding enclosure
(fuel box), caused the leak.
Failure of the second barrier (fuel box) is
a dormant failure, as this will only manifest
itself in case of connector (or fuel pipe
coupling) failure in flight.
This condition, if not corrected, could
result in a fire in the baggage compartment,
which would affect the aeroplane safe flight.
To address this potential unsafe condition,
Dassault Aviation issued Service Bulletin
(SB) F7X–284, which provides instructions to
restore the sealing of the Left Hand (LH) and
Right Hand (RH) fuel boxes.
For the reasons described above, this
[EASA] AD requires opening of the fuel
boxes and restoration of the sealing of the
fuel boxes to meet the initial design
specifications.
You may examine the MCAI in the
AD docket on the Internet at https://
www.regulations.gov by searching for
and locating Docket No. FAA–2015–
5813.
Related Service Information Under 1
CFR Part 51
Dassault Aviation has issued Service
Bulletin 7X–284, Revision 1, dated
E:\FR\FM\27NOP1.SGM
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]]>Agencies
[Federal Register Volume 80, Number 228 (Friday, November 27, 2015)]
[Proposed Rules]
[Pages 74052-74056]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2015-30120]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2015-5816; Directorate Identifier 2015-NM-029-AD]
RIN 2120-AA64
Airworthiness Directives; The Boeing Company Airplanes
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking (NPRM).
-----------------------------------------------------------------------
SUMMARY: We propose to supersede Airworthiness Directive (AD) 2006-10-
16, which applies to all The Boeing Company Model 747-100, 747-100B,
747-100B SUD, 747-200B, 747-200C, 747-200F, 747-300, 747-400, 747-400D,
747-400F, 747SR, and 747SP series airplanes. AD 2006-10-16 requires,
for certain airplanes, repetitive inspections for cracking of the
outboard and center sections of the horizontal stabilizer, and repair
if necessary. For certain other airplanes, AD 2006-10-16 requires a
detailed inspection to determine the type of fasteners, and related
investigative actions and repair if necessary. Since we issued AD 2006-
10-16, additional cracking was found in the splice plates, hinge
fittings, terminal fittings, the upper skin of the outboard and center
sections, and the rear spar webs before reaching the inspection
interval specified in AD 2006-10-16. Cracked and fractured Maraging
steel fasteners were also found. This proposed AD would reduce the
compliance time for certain inspections and would add repetitive
inspections for cracking of the splice plates, hinge fittings, terminal
fittings, the upper skin of the outboard and center sections, and the
rear spar webs in Zone B. This proposed AD would also add an inspection
to determine whether fasteners are magnetic in Zone C, repetitive
ultrasonic inspections for cracking and fractures of affected
fasteners, and related investigative and corrective actions if
necessary. This proposed AD would also add an optional modification,
which would terminate certain repetitive inspections, and would add
post-modification inspections and corrective action if necessary. We
are proposing this AD to detect and correct this cracking, which could
lead to reduced structural capability of the outboard and center
sections of the horizontal stabilizer and could result in loss of
control of the airplane.
DATES: We must receive comments on this proposed AD by January 11,
2016.
ADDRESSES: You may send comments, using the procedures found in 14 CFR
11.43 and 11.45, by any of the following methods:
Federal eRulemaking Portal: Go to https://www.regulations.gov. Follow the instructions for submitting comments.
Fax: 202-493-2251.
Mail: U.S. Department of Transportation, Docket
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New
Jersey Avenue SE., Washington, DC 20590.
Hand Delivery: Deliver to Mail address above between 9
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
For service information identified in this proposed AD, contact
Boeing Commercial Airplanes, Attention: Data & Services Management, P.
O. Box 3707, MC 2H-65, Seattle, WA 98124-2207; telephone: 206-544-5000,
extension 1; fax: 206-766-5680; Internet https://www.myboeingfleet.com.
You may view this referenced service information at the FAA, Transport
Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For information
on the availability of this material at the FAA, call 425-227-1221. It
is also available on the Internet at https://www.regulations.gov by
searching for and locating Docket No. FAA-2015-5816.
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-2015-
5816; or in person at the Docket Management Facility between 9 a.m. and
5 p.m., Monday through Friday, except Federal holidays. The AD docket
contains this proposed AD, the regulatory evaluation, any comments
received, and other information. The street address for the Docket
Office (phone: 800-647-5527) is in the ADDRESSES section. Comments will
be available in the AD docket shortly after receipt.
FOR FURTHER INFORMATION CONTACT: Nathan Weigand, Aerospace Engineer,
Airframe Branch, ANM-120S, FAA, Seattle Aircraft Certification Office,
1601 Lind Avenue SW., Renton, WA 98057-3356; phone: 425-917-6428; fax:
425-917-6590; email: nathan.p.weigand@faa.gov.
SUPPLEMENTARY INFORMATION:
Comments Invited
We invite you to send any written relevant data, views, or
arguments about
[[Page 74053]]
this proposed AD. Send your comments to an address listed under the
ADDRESSES section. Include ``Docket No. FAA-2015-5816; Directorate
Identifier 2015-NM-029-AD'' at the beginning of your comments. We
specifically invite comments on the overall regulatory, economic,
environmental, and energy aspects of this proposed AD. We will consider
all comments received by the closing date and may amend this proposed
AD because of those comments.
We will post all comments we receive, without change, to https://www.regulations.gov, including any personal information you provide. We
will also post a report summarizing each substantive verbal contact we
receive about this proposed AD.
Discussion
On May 8, 2006, we issued AD 2006-10-16, Amendment 39-14600 (71 FR
28570, May 17, 2006), for all The Boeing Company Model 747-100, 747-
100B, 747-100B SUD, 747-200B, 747-200C, 747-200F, 747-300, 747-400,
747-400D, 747-400F, 747SR, and 747SP series airplanes. AD 2006-10-16
requires, for certain airplanes, repetitive inspections for cracking of
the outboard and center sections of the horizontal stabilizer, and
repair if necessary. For certain other airplanes, AD 2006-10-16
requires a detailed inspection to determine the type of fasteners,
related investigative actions, and repair if necessary. AD 2006-10-16
resulted from reports of cracking in the outboard and center section of
the aft upper skin of the horizontal stabilizer, the rear spar chord,
rear spar web, terminal fittings, and splice plates; and a report of
fractured and cracked steel fasteners. We issued AD 2006-10-16 to
detect and correct this cracking, which could lead to reduced
structural capability of the outboard and center sections of the
horizontal stabilizer and could result in loss of control of the
airplane.
Actions Since AD 2006-10-16, Amendment 39-14600 (71 FR 28570, May 17,
2006), Was Issued
Since we issued AD 2006-10-16, Amendment 39-14600 (71 FR 28570, May
17, 2006), additional cracking was found in the splice plates, hinge
fittings, terminal fittings, the upper skin of the outboard and center
sections, and the rear spar webs before reaching the inspection
interval specified in AD 2006-10-16. Cracked and fractured Maraging
steel fasteners were also found.
Related Service Information Under 1 CFR Part 51
We reviewed Boeing Service Bulletin 747-55A2050, Revision 2, dated
January 23, 2015. The service information describes procedures for
accomplishing Zone A, Zone B, and Zone C inspections for cracking of
the upper skin and upper rear spar chord of the outboard and center
sections of the horizontal stabilizer, and related investigative and
corrective actions if necessary. The service information also describes
procedures for a magnetic inspection to determine the type of
fasteners, ultrasonic inspections for cracking and fractures of
affected fasteners, and related investigative actions and corrective
actions if necessary. The service information also describes procedures
for an optional modification, which would end certain repetitive
inspections, and procedures for post-modification inspections and
corrective action if necessary. 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 of this NPRM.
FAA's Determination
We are proposing this AD because we evaluated all the relevant
information and determined the unsafe condition described previously is
likely to exist or develop in other products of the same type design.
Proposed AD Requirements
Although this proposed AD does not explicitly restate the
requirements of AD 2006-10-16, Amendment 39-14600 (71 FR 28570, May 17,
2006), this proposed AD would retain all of the requirements. Those
requirements are referenced in the service information identified
previously, which, in turn, is referenced in paragraph (g) of this
proposed AD. This proposed AD would reduce the compliance time for
certain inspections and add new repetitive inspections for cracking of
the splice plates, hinge fittings, terminal fittings, the upper skin of
the outboard and center sections, and the rear spar webs in Zone B.
This proposed AD would also add an inspection to determine whether
fasteners are magnetic in Zone C (made of H-11 steel), repetitive
ultrasonic inspections for cracking and fractures of affected
fasteners, and related investigative and corrective actions if
necessary. This proposed AD would also add an optional modification,
which would end certain repetitive inspections, and procedures for
post-modification inspections and corrective action if necessary. This
proposed AD also adds optional open-hole NDT inspections (high
frequency eddy current inspections) for certain airplanes, for Zone B
inspections. This proposed AD would also require accomplishing the
actions specified in the service information described previously,
except as discussed under ``Difference Between this Proposed AD and the
Service Bulletin.'' For information on the procedures and compliance
times, see this service information at https://www.regulations.gov by
searching for and locating Docket No. FAA-2015-5816.
The phrase ``related investigative actions'' is used in this
proposed AD. ``Related investigative actions'' are follow-on actions
that (1) are related to the primary action, and (2) further investigate
the nature of any condition found. Related investigative actions in an
AD could include, for example, inspections.
The phrase ``corrective actions'' is used in this proposed AD.
``Corrective actions'' are actions that correct or address any
condition found. Corrective actions in an AD could include, for
example, repairs.
Difference Between This Proposed AD and the Service Bulletin
Although Boeing Service Bulletin 747-55A2050, Revision 2, dated
January 23, 2015, specifies that operators may contact the manufacturer
for disposition of certain repair conditions, this proposed AD would
require repairing those conditions in one of the following ways:
In accordance with a method that we approve; or
Using data that meet the certification basis of the
airplane, and that have been approved by the Boeing Commercial
Airplanes Organization Designation Authorization (ODA) whom we have
authorized to make those findings.
Costs of Compliance
We estimate that this proposed AD affects 116 airplanes of U.S.
registry.
We estimate the following costs to comply with this proposed AD:
[[Page 74054]]
Estimated Costs--Required Actions
----------------------------------------------------------------------------------------------------------------
Cost per Cost on U.S.
Action Labor cost Parts cost product operators
----------------------------------------------------------------------------------------------------------------
Zone A Inspections (required by AD 8 work-hours x $85 $0 $680 Up to $78,880.
2006-10-16, Amendment 39-14600). per hour = $680.
Zone B Open-hole NDT Inspection 30 work-hours x 85 0 2,550 Up to $295,800.
(required by AD 2006-10-16, per hour = 2,550.
Amendment 39-14600 for Groups 3,
4, and 5 airplanes; and for
Groups 1, 2, and 3 airplanes, if
done).
Zone C Maraging or H-11 Steel 8 work-hours x 85 per 0 680 Up to $78,880.
Fastener Inspection (required by hour = 680.
AD 2006-10-16, Amendment 39-14600
for Groups 1, 2, and 3 airplanes).
New Zone B proposed inspections... 248 work-hours x 85 0 21,080 $2,445,280.
per hour = 21,080.
New Zone C proposed inspection.... 26 work-hours x 85 0 2,210 $256,360.
per hour = 2,210.
----------------------------------------------------------------------------------------------------------------
Estimated Costs--Optional Actions
----------------------------------------------------------------------------------------------------------------
Action Labor cost Parts cost Cost per product
----------------------------------------------------------------------------------------------------------------
Open-hole NDT inspections (high Up to 298 work-hours x $$0.................... Up to $25,330.
frequency eddy current inspections. $85 per hour = up to
$25,330.
Zone B Modification.................. Up to 313 work-hours x Up to $3,486........... Up to $30,091.
$85 per hour = up to
$26,605.
Post-Modification Inspections........ Up to 298 work-hours x $0..................... Up to $25,330.
$85 per hour = up to
$25,330.
----------------------------------------------------------------------------------------------------------------
We have received no definitive data that would enable us to provide
a cost estimate for the on-condition actions specified in this proposed
AD.
Authority for This Rulemaking
Title 49 of the United States Code specifies the FAA's authority to
issue rules on aviation safety. Subtitle I, Section 106, describes the
authority of the FAA Administrator. Subtitle VII, Aviation Programs,
describes in more detail the scope of the Agency's authority.
We are issuing this rulemaking under the authority described in
Subtitle VII, Part A, Subpart III, Section 44701, ``General
requirements.'' Under that section, Congress charges the FAA with
promoting safe flight of civil aircraft in air commerce by prescribing
regulations for practices, methods, and procedures the Administrator
finds necessary for safety in air commerce. This regulation is within
the scope of that authority because it addresses an unsafe condition
that is likely to exist or develop on products identified in this
rulemaking action.
Regulatory Findings
We have determined that this proposed AD would not have federalism
implications under Executive Order 13132. This proposed AD would not
have a substantial direct effect on the States, on the relationship
between the national Government and the States, or on the distribution
of power and responsibilities among the various levels of government.
For the reasons discussed above, I certify that the proposed
regulation:
(1) Is not a ``significant regulatory action'' under Executive
Order 12866,
(2) Is not a ``significant rule'' under the DOT Regulatory Policies
and Procedures (44 FR 11034, February 26, 1979),
(3) Will not affect intrastate aviation in Alaska, and
(4) Will not have a significant economic impact, positive or
negative, on a substantial number of small entities under the criteria
of the Regulatory Flexibility Act.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.
The Proposed Amendment
Accordingly, under the authority delegated to me by the
Administrator, the FAA proposes to amend 14 CFR part 39 as follows:
PART 39--AIRWORTHINESS DIRECTIVES
0
1. The authority citation for part 39 continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
Sec. 39.13 [Amended]
0
2. The FAA amends Sec. 39.13 by removing Airworthiness Directive AD
2006-10-16, Amendment 39-14600 (71 FR 28570, May 17, 2006), and adding
the following new AD:
The Boeing Company: Docket No. FAA-2015-5816; Directorate Identifier
2015-NM-029-AD.
(a) Comments Due Date
The FAA must receive comments on this AD action by January 11,
2016.
(b) Affected ADs
This AD replaces AD 2006-10-16, Amendment 39-14600 (71 FR 28570,
May 17, 2006).
(c) Applicability
This AD applies to all The Boeing Company Model 747-100, 747-
100B, 747-100B SUD, 747-200B, 747-200C, 747-200F, 747-300, 747-400,
747-400D, 747-400F, 747SR, and 747SP series airplanes; certificated
in any category.
(d) Subject
Air Transport Association (ATA) of America Code 55, Stabilizers.
(e) Unsafe Condition
This AD was prompted by reports of cracking found in the splice
plates, hinge fittings, terminal fittings, the upper skin of the
outboard and center sections, and the rear spar webs before reaching
the inspection interval specified in AD 2006-10-16. Cracked and
fractured Maraging steel fasteners were also found. We are issuing
this AD to detect and correct this cracking, which
[[Page 74055]]
could lead to reduced structural capability of the outboard and
center sections of the horizontal stabilizer and could result in
loss of control of the airplane.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(g) Repetitive Inspections/Investigative and Corrective Actions
At the applicable time specified in paragraph 1.E.,
``Compliance,'' of Boeing Service Bulletin 747-55A2050, Revision 2,
dated January 23, 2015, except as required by paragraphs (h)(1) and
(h)(2) of this AD: Do the applicable actions specified in paragraphs
(g)(1), (g)(2), (g)(3), and (g)(4) of this AD, and all applicable
related investigative and corrective actions, in accordance with the
applicable part of the Accomplishment Instructions of Boeing Service
Bulletin 747-55A2050, Revision 2, dated January 23, 2015, except as
required by paragraph (h)(3) of this AD. Do all applicable related
investigative and corrective actions before further flight. Repeat
the applicable inspections specified in paragraphs (g)(1), (g)(2),
(g)(3), and (g)(4) of this AD at the applicable times specified in
paragraph 1.E., ``Compliance,'' of Boeing Service Bulletin 747-
55A2050, Revision 2, dated January 23, 2015.
(1) For Group 1 through 3 airplanes identified in Boeing Service
Bulletin 747-55A2050, Revision 2, dated January 23, 2015: Do non-
destructive test (NDT) inspections (ultrasonic, high frequency eddy
current, and low frequency eddy current inspections) or open-hole
NDT inspections (high frequency eddy current inspections), of Zone B
for cracking in accordance with Part 3 or Part 4 of the
Accomplishment Instructions of Boeing Service Bulletin 747-55A2050,
Revision 2, dated January 23, 2015, as applicable.
(2) For Group 4 through 6 airplanes identified in Boeing Service
Bulletin 747-55A2050, Revision 2, dated January 23, 2015: Do open-
hole NDT inspections (high frequency eddy current inspections), of
Zone B for cracking in accordance with Part 4 of the Accomplishment
Instructions of Boeing Service Bulletin 747-55A2050, Revision 2,
dated January 23, 2015.
(3) For Group 7 through 9 airplanes identified in Boeing Service
Bulletin 747-55A2050, Revision 2, dated January 23, 2015: Do
inspections of Zone A (detailed or high frequency eddy current
inspections) and Zone B (high frequency eddy current inspections)
for cracking, in accordance with Part 1, Part 2, or Part 4 of the
Accomplishment Instructions of Boeing Service Bulletin 747-55A2050,
Revision 2, dated January 23, 2015, as applicable.
(4) For Group 1 through 3 airplanes identified in Boeing Service
Bulletin 747-55A2050, Revision 2, dated January 23, 2015: Do an
inspection of Zone C Maraging or H-11 steel fasteners to determine
whether fasteners are magnetic, in accordance with Part 6 of the
Accomplishment Instructions of Boeing Service Bulletin 747-55A2050,
Revision 2, dated January 23, 2015.
(h) Exceptions to Service Bulletin Specifications
(1) Where Boeing Service Bulletin 747-55A2050, Revision 2, dated
January 23, 2015, specifies a compliance time ``after the Revision 2
date of this service bulletin,'' this AD requires compliance within
the specified compliance time after the effective date of this AD.
(2) The Condition column of Table 1 of paragraph 1.E.,
``Compliance,'' of Boeing Service Bulletin 747-55A2050, Revision 2,
dated January 23, 2015, refers to ``airplanes with certain total
flight cycles and total flight hours.'' This AD, however, applies to
the airplanes with the specified total flight cycles and total
flight hours as of the effective date of this AD.
(3) Where Boeing Service Bulletin 747-55A2050, Revision 2, dated
January 23, 2015, specifies to contact Boeing for repair
instructions: Before further flight, repair using a method approved
in accordance with the procedures specified in paragraph (l) of this
AD.
(i) Optional Terminating Action
(1) For Group 1 through 3 airplanes identified in Boeing Service
Bulletin 747-55A2050, Revision 2, dated January 23, 2015:
Accomplishing the Zone B modification, including all applicable
related investigative and corrective actions, specified in Part 7 of
the Accomplishment Instructions of Boeing Service Bulletin 747-
55A2050, Revision 2, dated January 23, 2015, except as required by
paragraph (h)(3) of this AD, terminates the repetitive inspections
specified in paragraphs (i)(1)(i) and (i)(1)(ii) of this AD for the
modified area only.
(i) Inspections required by paragraph (g)(1) of this AD for Zone
B, as specified in Part 3 and Part 4 of the Accomplishment
Instructions of Boeing Service Bulletin 747-55A2050, Revision 2,
dated January 23, 2015.
(ii) Inspections required by paragraph (g)(4) of this AD for
Zone C, as specified in Part 5 and Part 6 of the Accomplishment
Instructions of Boeing Service Bulletin 747-55A2050, Revision 2,
dated January 23, 2015.
(2) For Group 1 through 3 airplanes identified in Boeing Service
Bulletin 747-55A2050, Revision 2, dated January 23, 2015:
Accomplishing the Zone B open hole NDT inspection, repairing any
cracking as applicable, and replacing fasteners as specified in Part
4 of the Accomplishment Instructions of Boeing Service Bulletin 747-
55A2050, Revision 2, dated January 23, 2015, terminates the
repetitive ultrasonic inspections required by paragraph (g)(4) of
this AD for Zone C, as specified in Part 6 of the Accomplishment
Instructions of Boeing Service Bulletin 747-55A2050, Revision 2,
dated January 23, 2015, for the inspected area only.
(3) For Group 4 through 9 airplanes identified in Boeing Service
Bulletin 747-55A2050, Revision 2, dated January 23, 2015:
Accomplishing the Zone B modification, including all applicable
related investigative and corrective actions, specified in Part 7 of
the Accomplishment Instructions of Boeing Service Bulletin 747-
55A2050, Revision 2, dated January 23, 2015, except as required by
paragraph (h)(3) of this AD, terminates the repetitive inspections
required by paragraph (g)(2) or (g)(3) of this AD, as applicable,
only for Zone B, as specified in Part 4 of the Accomplishment
Instructions of Boeing Service Bulletin 747-55A2050, Revision 2,
dated January 23, 2015, for the modified area only.
(j) Repetitive Post-Modification Inspections and Corrective Actions
At the applicable time specified in paragraph 1.E.,
``Compliance,'' of Boeing Service Bulletin 747-55A2050, Revision 2,
dated January 23, 2015: Do the applicable inspections specified in
paragraphs (j)(1) and (j)(2) of this AD and all applicable
corrective actions, in accordance with Part 8 of the Accomplishment
Instructions of Boeing Service Bulletin 747-55A2050, Revision 2,
dated January 23, 2015, except as required by paragraph (h)(3) of
this AD. Do all applicable corrective actions before further flight.
Repeat the applicable inspections at the applicable times specified
in paragraph 1.E., ``Compliance,'' of Boeing Service Bulletin 747-
55A2050, Revision 2, dated January 23, 2015.
(1) For Group 1 through 3 airplanes identified in Boeing Service
Bulletin 747-55A2050, Revision 2, dated January 23, 2015 on which
the Zone B modification specified in paragraph (i)(1) of this AD is
done: Do non-destructive test (NDT) inspections (ultrasonic, high
frequency eddy current, and low frequency eddy current inspections)
or open-hole NDT inspections (high frequency eddy current
inspections) of Zone B for cracking.
(2) For Group 4 through 9 airplanes identified in Boeing Service
Bulletin 747-55A2050, Revision 2, dated January 23, 2015 on which
the Zone B modification specified in paragraph (i)(3) of this AD is
done: Do open-hole NDT inspections (high frequency eddy current
inspections) of Zone B for cracking.
(k) Parts Installation Prohibition
As of the effective date of this AD, no person may install any
Maraging or H-11 steel fasteners in the locations specified in this
AD. Where Boeing Service Bulletin 747-55A2050, Revision 2, dated
January 23, 2015, specifies to install H-11 bolts (kept fasteners),
this AD requires installation of Inconel bolts.
(l) Alternative Methods of Compliance (AMOCs)
(1) The Manager, Seattle Aircraft Certification Office (ACO),
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 ACO, send it to the
attention of the person identified in paragraph (m)(1) of this AD.
Information may be emailed to: 9-ANM-Seattle-ACO-AMOC-Requests@faa.gov.
(2) Before using any approved AMOC, notify your appropriate
principal inspector, or lacking a principal inspector, the manager
of the local flight standards district office/certificate holding
district office.
[[Page 74056]]
(3) An AMOC that provides an acceptable level of safety may be
used for any repair required by this AD if it is approved by the
Boeing Commercial Airplanes Organization Designation Authorization
(ODA) that has been authorized by the Manager, Seattle ACO, to make
those findings. For a repair method to be approved, the repair must
meet the certification basis of the airplane, and the approval must
specifically refer to this AD.
(4) AMOCs approved for AD 2006-10-16, Amendment 39-14600 (71 FR
28570, May 17, 2006), are approved as AMOCs for the corresponding
provisions of paragraph (g) of this AD, except for approved AMOCs
that allow installation of Maraging or H-11 steel fasteners.
(m) Related Information
(1) For more information about this AD, contact Nathan Weigand,
Aerospace Engineer, Airframe Branch, ANM-120S, FAA, Seattle ACO,
1601 Lind Avenue SW., Renton, WA 98057-3356; phone: 425-917-6428;
fax: 425-917-6590; email: nathan.p.weigand@faa.gov.
(2) For service information identified in this AD, contact
Boeing Commercial Airplanes, Attention: Data & Services Management,
P. O. Box 3707, MC 2H-65, Seattle, WA 98124-2207; telephone: 206-
544-5000, extension 1; fax: 206-766-5680; Internet https://www.myboeingfleet.com. You may view this referenced service
information at the FAA, Transport Airplane Directorate, 1601 Lind
Avenue SW., Renton, WA. For information on the availability of this
material at the FAA, call 425-227-1221.
Issued in Renton, Washington, on November 19, 2015.
Michael Kaszycki,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2015-30120 Filed 11-25-15; 8:45 am]
BILLING CODE 4910-13-P
