Airworthiness Directives; The Boeing Company Airplanes, 1254-1258 [2016-31367]
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Federal Register / Vol. 82, No. 3 / Thursday, January 5, 2017 / Proposed Rules
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 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, I certify
this 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 to the extent that it justifies
making a regulatory distinction; 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.
We prepared an economic evaluation
of the estimated costs to comply with
this proposed AD and placed it in the
AD docket.
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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:
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PART 39—AIRWORTHINESS
DIRECTIVES
1. The authority citation for part 39
continues to read as follows:
■
Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13
[Amended]
2. The FAA amends § 39.13 by adding
the following new airworthiness
directive (AD):
■
Airbus Helicopters Deutschland GmbH
Helicopters: Docket No. FAA–2016–
6928; Directorate Identifier 2016–SW–
018–AD.
(a) Applicability
This AD applies to Airbus Helicopters
Deutschland GmbH Helicopters Model MBB–
BK 117C–2 (including configuration C–2e)
helicopters, serial number 9004 through
9725, and Model MBB–BK 117D–2
helicopters, serial number 20003 through
20045, certificated in any category, with an
air inlet part number (P/N) B212M20C1005
installed.
(b) Unsafe Condition
This AD defines the unsafe condition as a
detached air inlet cover ring (ring), which
could become stuck between the air inlet and
the cyclic stick, restricting movement of the
cyclic stick. This condition could result in
loss of helicopter control.
(c) Comments Due Date
We must receive comments by March 6,
2017.
(d) Compliance
You are responsible for performing each
action required by this AD within the
specified compliance time unless it has
already been accomplished prior to that time.
(e) Required Actions
(1) Within 100 hours time-in-service (TIS),
manually inspect each ring to determine if it
is loose. If a ring is loose, before further
flight, glue the ring on the air inlet using an
adhesive (CM 687 or CM 6044 or equivalent)
as shown in Figure 1 of Airbus Helicopters
Alert Service Bulletin (ASB) MBB–BK117
C–2–21A–011, Revision 0, dated November
16, 2015 (ASB C–2–21A–011), or ASB MBB–
BK117 D–2–21A–004, Revision 0, dated
November 16, 2015 (ASB D–2–21A–004), as
applicable to your model helicopter. Rivet
the ring to the air inlet in accordance with
the Accomplishment Instructions, paragraphs
3.B.4.2 through 3.B.4.4 of ASB C–2–21A–011
or paragraphs 3.B.3.2 through 3.B.3.4 of ASB
D–2–21A–004.
(2) If a ring is not loose, within 400 hours
TIS:
(i) Manually inspect the ring to determine
if it is loose. If the ring is loose, before further
flight, glue the ring on the air inlet using an
adhesive (CM 687 or CM 6044 or equivalent)
as shown in Figure 1 of ASB C–2–21A–011
or ASB D–2–21A–004.
(ii) Rivet the ring to the air inlet in
accordance with the Accomplishment
Instructions, paragraphs 3.B.3.2 through
3.B.3.4 of ASB C–2–21A–011 or paragraphs
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3.B.2.2 through 3.B.2.4 of ASB D–2–21A–
004.
(3) After the effective date of this AD, do
not install an air inlet P/N B212M20C1005 on
any helicopter unless the ring has been
riveted to the air inlet in accordance with the
requirements of this AD.
(f) Alternative Methods of Compliance
(AMOCs)
(1) The Manager, Safety Management
Group, FAA, may approve AMOCs for this
AD. Send your proposal to: Matt Fuller,
Senior Aviation Safety Engineer, Safety
Management Group, Rotorcraft Directorate,
FAA, 10101 Hillwood Pkwy, Fort Worth, TX
76177; telephone (817) 222–5110; email 9ASW-FTW-AMOC-Requests@faa.gov.
(2) For operations conducted under a 14
CFR part 119 operating certificate or under
14 CFR part 91, subpart K, we suggest that
you notify your principal inspector, or
lacking a principal inspector, the manager of
the local flight standards district office or
certificate holding district office before
operating any aircraft complying with this
AD through an AMOC.
(g) Additional Information
The subject of this AD is addressed in
European Aviation Safety Agency (EASA) AD
No. 2016–0001, dated January 4, 2016. You
may view the EASA AD on the Internet at
https://www.regulations.gov in the AD Docket.
(h) Subject
Joint Aircraft Service Component (JASC)
Code: 2150, Cabin Cooling System.
Issued in Fort Worth, Texas, on December
21, 2016.
Lance T. Gant,
Manager, Rotorcraft Directorate, Aircraft
Certification Service.
[FR Doc. 2016–31865 Filed 1–4–17; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2016–9523; Directorate
Identifier 2016–NM–134–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) 2014–12–
13, which applies to all The Boeing
Company Model 737–100, –200, –200C,
–300, –400, and –500 series airplanes.
AD 2014–12–13 currently requires
repetitive inspections for cracking of the
main landing gear (MLG) beam, and the
SUMMARY:
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rear spar upper chord and rear spar web;
and repair if necessary. Since we issued
AD 2014–12–13, we received reports of
additional cracking in the inspar upper
skin, rear spar web and rear spar upper
chord. This proposed AD would expand
the inspection area and add related
investigative and corrective actions if
necessary. We are proposing this AD to
address the unsafe condition on these
products.
DATES: We must receive comments on
this proposed AD by February 21, 2017.
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 NPRM, contact Boeing Commercial
Airplanes, Attention: Contractual & Data
Services (C&DS), 2600 Westminster
Blvd., MC 110–SK57, Seal Beach, CA
90740; telephone 562–797–1717;
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–2016–
9523.
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–2016–
9523; 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:
Payman Soltani, Aerospace Engineer,
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Airframe Branch, ANM–120L, FAA, Los
Angeles Aircraft Certification Office
(ACO), 3960 Paramount Boulevard,
Lakewood, CA 90712–4137; phone:
562–627–5313; fax: 562–627–5210;
email: payman.soltani@faa.gov.
SUPPLEMENTARY INFORMATION:
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–2016–9523; Directorate Identifier
2016–NM–134–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 June 6, 2014, we issued AD 2014–
12–13, Amendment 39–17874 (79 FR
39300, July 10, 2014) (‘‘AD 2014–12–
13’’), for all The Boeing Company Model
737–100, –200, –200C, –300, –400, and
–500 series airplanes. AD 2014–12–13
requires repetitive inspections for
cracking of the aft support fitting for the
MLG beam, the rear spar upper chord
and rear spar web in the area of rear
spar station (RSS) 224.14; and repair if
necessary. AD 2014–12–13 resulted
from reports of cracks found in the aft
support fitting, the rear spar upper
chord, and the rear spar web. We issued
AD 2014–12–13 to detect and correct
cracking of the aft support fitting for the
MLG beam, the rear spar upper chord
and rear spar web in the area of RSS
224.14, which could grow and result in
a fuel leak and possible fire.
Other Related Rulemaking
On October 11, 2015, we issued AD
2015–21–08, Amendment 39–18301 (80
FR 65921, October 28, 2015) (‘‘AD
2015–21–08’’), for certain The Boeing
Company Model 737–100, –200, –200C,
–300, –400, and –500 series airplanes.
AD 2015–21–08 was prompted by a
report that an operator discovered a
crack in a certain section of the inspar
upper skin, just forward of the rear spar
on the right wing. AD 2015–21–08
requires repetitive eddy current
inspections for any cracking in the
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inspar upper skin, and related
investigative and corrective actions if
necessary. We issued AD 2015–21–08 to
detect and correct any cracking in the
inspar upper skin and rear spar upper
chord, which could result in the
inability of the structure to carry limit
load, or result in a fuel leak, which
could prevent continued safe flight and
landing.
Actions Since AD 2014–12–13 and
2015–21–08 Were Issued
Since we issued AD 2014–12–13 and
AD 2015–21–08, an operator discovered
a 2.375-inch-long crack in the inspar
upper skin at wing buttock line (WBL)
157, just forward of the rear spar on the
right wing and adjacent to the
inspection area specified in Boeing
Special Attention Service Bulletin 737–
57–1318, dated May 15, 2013 (the
source of service information for the
actions required by AD 2014–12–13).
Two additional smaller cracks were
found in the skin at two holes common
to the rear spar in the same area.
Subsequent inspections revealed that
the right rear spar upper chord was
almost completely severed and the left
rear spar chord was completely severed.
Rear spar web cracks were also noted on
both wings. The affected airplane had
accumulated 51,548 total flight cycles.
After the initial report of the inspar
upper skin crack, additional reports of
inspar upper skin cracking were found
in the same area. Inspar upper skin
cracking at this location is the subject of
AD 2015–21–08, which correlates with
Boeing Alert Service Bulletin 737–
57A1326, dated September 22, 2015;
and Boeing Alert Service Bulletin 737–
57A1328, dated July 22, 2016. Although
skin cracking is addressed outside of
Boeing Special Attention Service
Bulletin 737–57–1318, dated May 15,
2013, analysis shows that rear spar
upper chord cracking can negatively
influence the inspar upper skin cracking
condition. In addition to influencing
skin cracking, rear spar upper chord
cracking can also influence cracking at
other mating structures.
In addition, since Boeing Alert
Service Bulletin 737–57A1318, dated
May 15, 2013, has been issued, multiple
operators have also reported cracking in
the MLG beam forward support fitting,
which was found while doing repairs to
address cracked chords. Therefore, the
MLG beam forward support fitting has
been added to the inspection area, and
the inspection threshold and intervals
have been shortened, as specified in
Boeing Alert Service Bulletin 737–
57A1318, Revision 1, dated July 22,
2016.
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Federal Register / Vol. 82, No. 3 / Thursday, January 5, 2017 / Proposed Rules
Related Service Information Under 1
CFR Part 51
We reviewed Boeing Alert Service
Bulletin 737–57A1318, Revision 1,
dated July 22, 2016. The service
information describes procedures for
repetitive high frequency eddy current
(HFEC) open hole inspections for any
cracking in the forward support fitting,
the aft support fitting, the rear spar
upper chord, and the rear spar web at
the 12 fastener holes (locations 1–12).
The service information also describes
the option of HFEC open hole
inspections for any cracking in the
forward support fitting and the aft
support fitting, and HFEC surface
inspections for any cracking in the rear
spar upper chord and rear spar upper
web, as applicable, and related
investigative and corrective actions.
We also reviewed Boeing Alert
Service Bulletin 737–57A1328, dated
July 22, 2016. The service information
describes procedures for repetitive eddy
current inspections of the left and right
wing for any cracking in the inspar
upper skin and the repair parts if
applicable, and related investigative and
corrective actions.
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.
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.
an AD could include, for example,
inspections.
The phrase ‘‘corrective actions’’ is
used in this proposed AD. Corrective
actions correct or address any condition
found. Corrective actions in an AD
could include, for example, repairs.
Proposed AD Requirements
Although this proposed AD does not
explicitly restate the requirements of AD
2014–12–13, this proposed AD would
retain all of the requirements of AD
2014–12–13. Those requirements are
referenced in the service information
identified previously, which, in turn, is
referenced in paragraphs (g) and (h) of
this proposed AD. This proposed AD
would also require accomplishing the
actions specified in the service
information described previously,
except as discussed under ‘‘Differences
Between this Proposed AD and the
Service Information.’’ 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–2016–
9523.
The phrase ‘‘related investigative
actions’’ is used in this proposed AD.
Related investigative actions are followon actions that (1) are related to the
primary action, and (2) further
investigate the nature of any condition
found. Related investigative actions in
Differences Between This Proposed AD
and the Service Information
Boeing Alert Service Bulletin 737–
57A1318, Revision 1, dated July 22,
2016; and Boeing Alert Service Bulletin
737–57A1328, dated July 22, 2016;
specify to contact the manufacturer for
certain instructions, but this proposed
AD would require accomplishment of
repair methods, modification
deviations, and alteration deviations 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 471 airplanes of U.S. registry. We
estimate the following costs to comply
with this proposed AD:
ESTIMATED COSTS
Action
HFEC open hole inspections ....
Eddy current inspection .............
Parts
cost
Labor cost
82 work-hours
= $6,970
cycle.
14 work-hours
= $1,190
cycle.
Cost per product
Cost on U.S. operators
× $85 per hour
per inspection
$0
$6,970 per inspection cycle .....
$3,282,870 per inspection
cycle.
× $85 per hour
per inspection
0
$1,190 per inspection cycle .....
$560,490 per inspection cycle.
ESTIMATED COSTS FOR OPTIONAL ACTIONS
Parts
cost
Labor cost
Inspection ...............................
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Action
Up to 41 work-hours × $85 per hour = $3,485 per
inspection cycle.
We have received no definitive data
that would enable us to provide cost
estimates 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,
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$0
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
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Cost per product
Up to $1,641,435 per inspection cycle.
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
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Federal Register / Vol. 82, No. 3 / Thursday, January 5, 2017 / Proposed Rules
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
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
removing Airworthiness Directive (AD)
2014–12–13, Amendment 39–17874 (79
FR 39300, July 10, 2014), and adding the
following new AD:
■
The Boeing Company: Docket No. FAA–
2016–9523; Directorate Identifier 2016–
NM–134–AD.
(a) Comments Due Date
The FAA must receive comments on this
AD action by February 21, 2017.
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(b) Affected ADs
This AD replaces AD 2014–12–13,
Amendment 39–17874 (79 FR 39300, July 10,
2014). This AD affects AD 2015–21–08,
Amendment 39–18301 (80 FR 65921, October
28, 2015).
(c) Applicability
This AD applies to all The Boeing
Company Model 737–100, –200, –200C,
–300, –400, and –500 series airplanes,
certificated in any category.
(d) Subject
Air Transport Association (ATA) of
America Code 57, Wings.
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(e) Unsafe Condition
This AD was prompted by reports of
additional cracking in the inspar upper skin
at Wing Buttock Line (WBL) 157 and in the
skin at two holes common to the rear spar in
the same area, and rear spar web cracks were
also noted on both wings. Subsequent
inspections revealed that the right rear spar
upper chord was almost completely severed
and the left rear spar upper chord was
completely severed. We are issuing this AD
to detect and correct cracking of the forward
and aft support fittings for the main landing
gear (MLG) beam, the rear spar upper chord
and rear spar web in the area of rear spar
station (RSS) 224.14, which could grow and
result in a fuel leak and possible fire.
(f) Compliance
Comply with this AD within the
compliance times specified, unless already
done.
(g) Required Actions for Group 1 Airplanes
For airplanes identified as Group 1 in
Boeing Alert Service Bulletin 737–57A1318,
Revision 1, dated July 22, 2016: At the
applicable time specified in table 1 of
paragraph 1.E., ‘‘Compliance,’’ of Boeing
Alert Service Bulletin 737–57A1318,
Revision 1, dated July 22, 2016, except as
required by paragraph (j)(3) of this AD, do
applicable inspections and corrective actions
using a method approved in accordance with
the procedures specified in paragraph (m) of
this AD.
(h) Required Actions for Groups 2–7
Airplanes
For airplanes identified as Groups 2–7 in
Boeing Alert Service Bulletin 737–57A1318,
Revision 1, dated July 22, 2016: At the
applicable time specified in table 2 through
table 9 of paragraph 1.E., ‘‘Compliance,’’ of
Boeing Alert Service Bulletin 737–57A1318,
Revision 1, dated July 22, 2016, except as
required by paragraph (j)(3) of this AD: Do
high frequency eddy current (HFEC) open
hole inspections for any cracking in the
forward support fitting, the aft support
fitting, the rear spar upper chord, and the
rear spar web at the 12 fastener holes
(locations 1–12); or HFEC open hole
inspections for any cracking in the forward
support fitting and the aft support fitting, and
HFEC surface inspection for any cracking in
the rear spar upper chord and rear spar upper
web; as applicable, and do all applicable
related investigative and corrective actions,
in accordance with the Accomplishment
Instructions of Boeing Alert Service Bulletin
737–57A1318, Revision 1, dated July 22,
2016. Do all applicable related investigative
and corrective actions before further flight.
Thereafter, repeat the HFEC inspection at the
applicable time specified in table 2 through
table 9 of paragraph 1.E., ‘‘Compliance,’’ of
Boeing Alert Service Bulletin 737–57A1318,
Revision 1, dated July 22, 2016. Options
provided in Boeing Alert Service Bulletin
737–57A1318, Revision 1, dated July 22,
2016, for accomplishing the inspection are
acceptable for the corresponding
requirements of this paragraph provided that
the inspections are done at the applicable
times in paragraph 1.E., ‘‘Compliance,’’ of
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Boeing Alert Service Bulletin 737–57A1318,
Revision 1, dated July 22, 2016.
(i) Eddy Current Inspection
For airplanes identified in Boeing Alert
Service Bulletin 737–57A1328, dated July 22,
2016: At the applicable time specified in
table 1 and table 2 of paragraph 1.E.,
‘‘Compliance,’’ of Boeing Alert Service
Bulletin 737–57A1328, dated July 22, 2016,
except as required by paragraph (j)(2) of this
AD, do an eddy current inspection of the left
and right wings for any cracking in the inspar
upper skin, and at the repair parts if
applicable, and do all applicable related
investigative and corrective actions, in
accordance with the Accomplishment
Instructions of Boeing Alert Service Bulletin
737–57A1328, dated July 22, 2016. Do all
related investigative and corrective actions
before further flight. Thereafter, repeat the
eddy current inspection at the applicable
time specified in table 1 and table 2 of
paragraph 1.E., ‘‘Compliance,’’ of Boeing
Alert Service Bulletin 737–57A1328, dated
July 22, 2016.
(j) Exceptions to the Service Information
(1) If any cracking is found during any
inspection required by this AD, and Boeing
Alert Service Bulletin 737–57A1328, dated
July 22, 2016, specifies to contact Boeing for
appropriate action: Before further flight,
repair using a method approved in
accordance with the procedures specified in
paragraph (m) of this AD.
(2) Where Boeing Alert Service Bulletin
737–57A1328, dated July 22, 2016, specifies
a compliance time ‘‘after the Original Issue
date of this service bulletin,’’ paragraph (i) of
this AD requires compliance within the
specified compliance time after the effective
date of this AD.
(3) Where Boeing Alert Service Bulletin
737–57A1318, Revision 1, dated July 22,
2016, specifies a compliance time ‘‘after the
Revision 1 date of this service bulletin,
whichever occurs later,’’ paragraphs (g) and
(h) of this AD require compliance within the
specified compliance time after the effective
date of this AD.
(k) Terminating Action
Accomplishing the initial inspections and
applicable related investigative and
corrective actions required by paragraphs (g),
(h), and (i) of this AD, as applicable, in
accordance with the Accomplishment
Instructions of Boeing Alert Service Bulletin
737–57A1318, Revision 1, dated July 22,
2016; and Boeing Alert Service Bulletin 737–
57A1328, dated July 22, 2016, terminates all
requirements of AD 2015–21–08.
(l) Credit for Previous Actions
This paragraph provides credit for the
actions specified in paragraphs (g) and (h) of
this AD, if those actions were performed
before the effective date of this AD using
Boeing Alert Service Bulletin 737–57A1318,
May 15, 2013, which was incorporated by
reference in AD 2014–03–06, Amendment
39–17743 (79 FR 39300, July 10, 2014).
E:\FR\FM\05JAP1.SGM
05JAP1
1258
Federal Register / Vol. 82, No. 3 / Thursday, January 5, 2017 / Proposed Rules
mstockstill on DSK3G9T082PROD with PROPOSALS
(m) Alternative Methods of Compliance
(AMOCs)
(1) The Manager, Los Angeles Aircraft
Certification Office (ACO), ANM–120L, 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 (n)(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, Los Angeles
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) Except as required by paragraph (j) of
this AD: For service information that
contains steps that are labeled as Required
for Compliance (RC), the provisions of
paragraphs (m)(4)(i) and (m)(4)(ii) of this AD
apply.
(i) The steps labeled as RC, including
substeps under an RC step and any figures
identified in an RC step, must be done to
comply with the AD. If a step or sub-step is
labeled ‘‘RC Exempt,’’ then the RC
requirement is removed from that step or
sub-step. An AMOC is required for any
deviations to RC steps, including substeps
and identified figures.
(ii) Steps not labeled as RC may be
deviated from using accepted methods in
accordance with the operator’s maintenance
or inspection program without obtaining
approval of an AMOC, provided the RC steps,
including substeps and identified figures, can
still be done as specified, and the airplane
can be put back in an airworthy condition.
Issued in Renton, Washington, on
December 16, 2016.
Ross Landes,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. 2016–31367 Filed 1–4–17; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2016–9380; Directorate
Identifier 2016–NE–21–AD]
RIN 2120–AA64
Airworthiness Directives; CFE
Company Turbofan Engines
Federal Aviation
Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
We propose to adopt a new
airworthiness directive (AD) for certain
CFE Company (CFE) turbofan engines.
This proposed AD was prompted by a
quality escape for high-pressure
compressor (HPC) impellers made from
forgings with nonconforming material
grain size. This proposed AD would
require removal of the HPC impeller.
We are proposing this AD to correct the
unsafe condition on these products.
DATES: We must receive comments on
this proposed AD by February 21, 2017.
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,
(n) Related Information
M–30, West Building Ground Floor,
(1) For more information about this AD,
Room W12–140, 1200 New Jersey
contact Payman Soltani, Aerospace Engineer, Avenue SE., Washington, DC 20590.
Airframe Branch, ANM–120L, FAA, Los
• Hand Delivery: Deliver to Mail
Angeles ACO, 3960 Paramount Boulevard,
address above between 9 a.m. and 5
Lakewood, CA 90712–4137; phone: 562–627–
p.m., Monday through Friday, except
5313; fax: 562–627–5210; email:
Federal holidays.
payman.soltani@faa.gov.
For service information identified in
(2) For service information identified in
this AD, contact Boeing Commercial
this NPRM, contact CFE Company, 111
Airplanes, Attention: Contractual & Data
S. 34th Street, Phoenix, Arizona 85034–
Services (C&DS), 2600 Westminster Blvd.,
2802; phone: 800–601–3099; Internet:
MC 110–SK57, Seal Beach, CA 90740;
https://www.myaerospace.com. You
telephone 562–797–1717; Internet https://
may view this referenced service
www.myboeingfleet.com. You may view this
information at the FAA, Engine &
referenced service information at the FAA,
Propeller Directorate, 1200 District
Transport Airplane Directorate, 1601 Lind
Avenue, Burlington, MA. For
Avenue SW., Renton, WA. For information
information on the availability of this
on the availability of this material at the
FAA, call 425–227–1221.
material at the FAA, call 781–238–7125.
VerDate Sep<11>2014
20:07 Jan 04, 2017
Jkt 241001
SUMMARY:
PO 00000
Frm 00028
Fmt 4702
Sfmt 4702
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–2016–
9380; 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:
Martin Adler, Aerospace Engineer,
Engine Certification Office, FAA, 1200
District Avenue, Burlington, MA 01803;
phone: 781–238–7157; fax: 781–238–
7199; email: martin.adler@faa.gov.
SUPPLEMENTARY INFORMATION:
Comments Invited
We invite you to send any written
relevant data, views, or arguments about
this proposal. Send your comments to
an address listed under the ADDRESSES
section. Include ‘‘Docket No. FAA–
2016–9380; Directorate Identifier 2016–
NE–21–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
We propose to adopt an AD for certain
CFE CFE738–1–1B model turbofan
engines with HPC impeller, part number
(P/N) 6079T77P07 or P/N 6079T77P09
installed. This proposed AD was
prompted by a quality escape for HPC
impellers made from forgings with
nonconforming material grain size. This
condition, if not corrected, could result
in failure of the HPC impeller, damage
to the engine, and damage to the
airplane.
Related Service Information Under
1 CFR Part 51
We reviewed CFE Service Bulletin
(SB) CFE738–72–8080, Revision 0,
dated August 18, 2016. The SB
E:\FR\FM\05JAP1.SGM
05JAP1
]]>Agencies
[Federal Register Volume 82, Number 3 (Thursday, January 5, 2017)]
[Proposed Rules]
[Pages 1254-1258]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2016-31367]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2016-9523; Directorate Identifier 2016-NM-134-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) 2014-12-
13, which applies to all The Boeing Company Model 737-100, -200, -200C,
-300, -400, and -500 series airplanes. AD 2014-12-13 currently requires
repetitive inspections for cracking of the main landing gear (MLG)
beam, and the
[[Page 1255]]
rear spar upper chord and rear spar web; and repair if necessary. Since
we issued AD 2014-12-13, we received reports of additional cracking in
the inspar upper skin, rear spar web and rear spar upper chord. This
proposed AD would expand the inspection area and add related
investigative and corrective actions if necessary. We are proposing
this AD to address the unsafe condition on these products.
DATES: We must receive comments on this proposed AD by February 21,
2017.
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 NPRM, contact Boeing
Commercial Airplanes, Attention: Contractual & Data Services (C&DS),
2600 Westminster Blvd., MC 110-SK57, Seal Beach, CA 90740; telephone
562-797-1717; 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-2016-9523.
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-2016-
9523; 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: Payman Soltani, Aerospace Engineer,
Airframe Branch, ANM-120L, FAA, Los Angeles Aircraft Certification
Office (ACO), 3960 Paramount Boulevard, Lakewood, CA 90712-4137; phone:
562-627-5313; fax: 562-627-5210; email: payman.soltani@faa.gov.
SUPPLEMENTARY INFORMATION:
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-2016-9523;
Directorate Identifier 2016-NM-134-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 June 6, 2014, we issued AD 2014-12-13, Amendment 39-17874 (79 FR
39300, July 10, 2014) (``AD 2014-12-13''), for all The Boeing Company
Model 737-100, -200, -200C, -300, -400, and -500 series airplanes. AD
2014-12-13 requires repetitive inspections for cracking of the aft
support fitting for the MLG beam, the rear spar upper chord and rear
spar web in the area of rear spar station (RSS) 224.14; and repair if
necessary. AD 2014-12-13 resulted from reports of cracks found in the
aft support fitting, the rear spar upper chord, and the rear spar web.
We issued AD 2014-12-13 to detect and correct cracking of the aft
support fitting for the MLG beam, the rear spar upper chord and rear
spar web in the area of RSS 224.14, which could grow and result in a
fuel leak and possible fire.
Other Related Rulemaking
On October 11, 2015, we issued AD 2015-21-08, Amendment 39-18301
(80 FR 65921, October 28, 2015) (``AD 2015-21-08''), for certain The
Boeing Company Model 737-100, -200, -200C, -300, -400, and -500 series
airplanes. AD 2015-21-08 was prompted by a report that an operator
discovered a crack in a certain section of the inspar upper skin, just
forward of the rear spar on the right wing. AD 2015-21-08 requires
repetitive eddy current inspections for any cracking in the inspar
upper skin, and related investigative and corrective actions if
necessary. We issued AD 2015-21-08 to detect and correct any cracking
in the inspar upper skin and rear spar upper chord, which could result
in the inability of the structure to carry limit load, or result in a
fuel leak, which could prevent continued safe flight and landing.
Actions Since AD 2014-12-13 and 2015-21-08 Were Issued
Since we issued AD 2014-12-13 and AD 2015-21-08, an operator
discovered a 2.375-inch-long crack in the inspar upper skin at wing
buttock line (WBL) 157, just forward of the rear spar on the right wing
and adjacent to the inspection area specified in Boeing Special
Attention Service Bulletin 737-57-1318, dated May 15, 2013 (the source
of service information for the actions required by AD 2014-12-13). Two
additional smaller cracks were found in the skin at two holes common to
the rear spar in the same area. Subsequent inspections revealed that
the right rear spar upper chord was almost completely severed and the
left rear spar chord was completely severed. Rear spar web cracks were
also noted on both wings. The affected airplane had accumulated 51,548
total flight cycles.
After the initial report of the inspar upper skin crack, additional
reports of inspar upper skin cracking were found in the same area.
Inspar upper skin cracking at this location is the subject of AD 2015-
21-08, which correlates with Boeing Alert Service Bulletin 737-57A1326,
dated September 22, 2015; and Boeing Alert Service Bulletin 737-
57A1328, dated July 22, 2016. Although skin cracking is addressed
outside of Boeing Special Attention Service Bulletin 737-57-1318, dated
May 15, 2013, analysis shows that rear spar upper chord cracking can
negatively influence the inspar upper skin cracking condition. In
addition to influencing skin cracking, rear spar upper chord cracking
can also influence cracking at other mating structures.
In addition, since Boeing Alert Service Bulletin 737-57A1318, dated
May 15, 2013, has been issued, multiple operators have also reported
cracking in the MLG beam forward support fitting, which was found while
doing repairs to address cracked chords. Therefore, the MLG beam
forward support fitting has been added to the inspection area, and the
inspection threshold and intervals have been shortened, as specified in
Boeing Alert Service Bulletin 737-57A1318, Revision 1, dated July 22,
2016.
[[Page 1256]]
Related Service Information Under 1 CFR Part 51
We reviewed Boeing Alert Service Bulletin 737-57A1318, Revision 1,
dated July 22, 2016. The service information describes procedures for
repetitive high frequency eddy current (HFEC) open hole inspections for
any cracking in the forward support fitting, the aft support fitting,
the rear spar upper chord, and the rear spar web at the 12 fastener
holes (locations 1-12). The service information also describes the
option of HFEC open hole inspections for any cracking in the forward
support fitting and the aft support fitting, and HFEC surface
inspections for any cracking in the rear spar upper chord and rear spar
upper web, as applicable, and related investigative and corrective
actions.
We also reviewed Boeing Alert Service Bulletin 737-57A1328, dated
July 22, 2016. The service information describes procedures for
repetitive eddy current inspections of the left and right wing for any
cracking in the inspar upper skin and the repair parts if applicable,
and related investigative and corrective actions.
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.
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 2014-12-13, this proposed AD would retain all of the
requirements of AD 2014-12-13. Those requirements are referenced in the
service information identified previously, which, in turn, is
referenced in paragraphs (g) and (h) of this proposed AD. This proposed
AD would also require accomplishing the actions specified in the
service information described previously, except as discussed under
``Differences Between this Proposed AD and the Service Information.''
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-2016-9523.
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 correct or address any condition found. Corrective
actions in an AD could include, for example, repairs.
Differences Between This Proposed AD and the Service Information
Boeing Alert Service Bulletin 737-57A1318, Revision 1, dated July
22, 2016; and Boeing Alert Service Bulletin 737-57A1328, dated July 22,
2016; specify to contact the manufacturer for certain instructions, but
this proposed AD would require accomplishment of repair methods,
modification deviations, and alteration deviations 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 471 airplanes of U.S.
registry. We estimate the following costs to comply with this proposed
AD:
Estimated Costs
----------------------------------------------------------------------------------------------------------------
Parts Cost on U.S.
Action Labor cost cost Cost per product operators
----------------------------------------------------------------------------------------------------------------
HFEC open hole inspections........ 82 work-hours x $85 $0 $6,970 per inspection $3,282,870 per
per hour = $6,970 cycle. inspection cycle.
per inspection cycle.
Eddy current inspection........... 14 work-hours x $85 0 $1,190 per inspection $560,490 per
per hour = $1,190 cycle. inspection cycle.
per inspection cycle.
----------------------------------------------------------------------------------------------------------------
Estimated Costs for Optional Actions
------------------------------------------------------------------------
Parts Cost per
Action Labor cost cost product
------------------------------------------------------------------------
Inspection.................. Up to 41 work- $0 Up to
hours x $85 $1,641,435 per
per hour = inspection
$3,485 per cycle.
inspection
cycle.
------------------------------------------------------------------------
We have received no definitive data that would enable us to provide
cost estimates 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
[[Page 1257]]
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)
2014-12-13, Amendment 39-17874 (79 FR 39300, July 10, 2014), and adding
the following new AD:
The Boeing Company: Docket No. FAA-2016-9523; Directorate Identifier
2016-NM-134-AD.
(a) Comments Due Date
The FAA must receive comments on this AD action by February 21,
2017.
(b) Affected ADs
This AD replaces AD 2014-12-13, Amendment 39-17874 (79 FR 39300,
July 10, 2014). This AD affects AD 2015-21-08, Amendment 39-18301
(80 FR 65921, October 28, 2015).
(c) Applicability
This AD applies to all The Boeing Company Model 737-100, -200, -
200C, -300, -400, and -500 series airplanes, certificated in any
category.
(d) Subject
Air Transport Association (ATA) of America Code 57, Wings.
(e) Unsafe Condition
This AD was prompted by reports of additional cracking in the
inspar upper skin at Wing Buttock Line (WBL) 157 and in the skin at
two holes common to the rear spar in the same area, and rear spar
web cracks were also noted on both wings. Subsequent inspections
revealed that the right rear spar upper chord was almost completely
severed and the left rear spar upper chord was completely severed.
We are issuing this AD to detect and correct cracking of the forward
and aft support fittings for the main landing gear (MLG) beam, the
rear spar upper chord and rear spar web in the area of rear spar
station (RSS) 224.14, which could grow and result in a fuel leak and
possible fire.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(g) Required Actions for Group 1 Airplanes
For airplanes identified as Group 1 in Boeing Alert Service
Bulletin 737-57A1318, Revision 1, dated July 22, 2016: At the
applicable time specified in table 1 of paragraph 1.E.,
``Compliance,'' of Boeing Alert Service Bulletin 737-57A1318,
Revision 1, dated July 22, 2016, except as required by paragraph
(j)(3) of this AD, do applicable inspections and corrective actions
using a method approved in accordance with the procedures specified
in paragraph (m) of this AD.
(h) Required Actions for Groups 2-7 Airplanes
For airplanes identified as Groups 2-7 in Boeing Alert Service
Bulletin 737-57A1318, Revision 1, dated July 22, 2016: At the
applicable time specified in table 2 through table 9 of paragraph
1.E., ``Compliance,'' of Boeing Alert Service Bulletin 737-57A1318,
Revision 1, dated July 22, 2016, except as required by paragraph
(j)(3) of this AD: Do high frequency eddy current (HFEC) open hole
inspections for any cracking in the forward support fitting, the aft
support fitting, the rear spar upper chord, and the rear spar web at
the 12 fastener holes (locations 1-12); or HFEC open hole
inspections for any cracking in the forward support fitting and the
aft support fitting, and HFEC surface inspection for any cracking in
the rear spar upper chord and rear spar upper web; as applicable,
and do all applicable related investigative and corrective actions,
in accordance with the Accomplishment Instructions of Boeing Alert
Service Bulletin 737-57A1318, Revision 1, dated July 22, 2016. Do
all applicable related investigative and corrective actions before
further flight. Thereafter, repeat the HFEC inspection at the
applicable time specified in table 2 through table 9 of paragraph
1.E., ``Compliance,'' of Boeing Alert Service Bulletin 737-57A1318,
Revision 1, dated July 22, 2016. Options provided in Boeing Alert
Service Bulletin 737-57A1318, Revision 1, dated July 22, 2016, for
accomplishing the inspection are acceptable for the corresponding
requirements of this paragraph provided that the inspections are
done at the applicable times in paragraph 1.E., ``Compliance,'' of
Boeing Alert Service Bulletin 737-57A1318, Revision 1, dated July
22, 2016.
(i) Eddy Current Inspection
For airplanes identified in Boeing Alert Service Bulletin 737-
57A1328, dated July 22, 2016: At the applicable time specified in
table 1 and table 2 of paragraph 1.E., ``Compliance,'' of Boeing
Alert Service Bulletin 737-57A1328, dated July 22, 2016, except as
required by paragraph (j)(2) of this AD, do an eddy current
inspection of the left and right wings for any cracking in the
inspar upper skin, and at the repair parts if applicable, and do all
applicable related investigative and corrective actions, in
accordance with the Accomplishment Instructions of Boeing Alert
Service Bulletin 737-57A1328, dated July 22, 2016. Do all related
investigative and corrective actions before further flight.
Thereafter, repeat the eddy current inspection at the applicable
time specified in table 1 and table 2 of paragraph 1.E.,
``Compliance,'' of Boeing Alert Service Bulletin 737-57A1328, dated
July 22, 2016.
(j) Exceptions to the Service Information
(1) If any cracking is found during any inspection required by
this AD, and Boeing Alert Service Bulletin 737-57A1328, dated July
22, 2016, specifies to contact Boeing for appropriate action: Before
further flight, repair using a method approved in accordance with
the procedures specified in paragraph (m) of this AD.
(2) Where Boeing Alert Service Bulletin 737-57A1328, dated July
22, 2016, specifies a compliance time ``after the Original Issue
date of this service bulletin,'' paragraph (i) of this AD requires
compliance within the specified compliance time after the effective
date of this AD.
(3) Where Boeing Alert Service Bulletin 737-57A1318, Revision 1,
dated July 22, 2016, specifies a compliance time ``after the
Revision 1 date of this service bulletin, whichever occurs later,''
paragraphs (g) and (h) of this AD require compliance within the
specified compliance time after the effective date of this AD.
(k) Terminating Action
Accomplishing the initial inspections and applicable related
investigative and corrective actions required by paragraphs (g),
(h), and (i) of this AD, as applicable, in accordance with the
Accomplishment Instructions of Boeing Alert Service Bulletin 737-
57A1318, Revision 1, dated July 22, 2016; and Boeing Alert Service
Bulletin 737-57A1328, dated July 22, 2016, terminates all
requirements of AD 2015-21-08.
(l) Credit for Previous Actions
This paragraph provides credit for the actions specified in
paragraphs (g) and (h) of this AD, if those actions were performed
before the effective date of this AD using Boeing Alert Service
Bulletin 737-57A1318, May 15, 2013, which was incorporated by
reference in AD 2014-03-06, Amendment 39-17743 (79 FR 39300, July
10, 2014).
[[Page 1258]]
(m) Alternative Methods of Compliance (AMOCs)
(1) The Manager, Los Angeles Aircraft Certification Office
(ACO), ANM-120L, 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 (n)(1) of
this AD. Information may be emailed to: 9-ANM-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.
(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, Los Angeles 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) Except as required by paragraph (j) of this AD: For service
information that contains steps that are labeled as Required for
Compliance (RC), the provisions of paragraphs (m)(4)(i) and
(m)(4)(ii) of this AD apply.
(i) The steps labeled as RC, including substeps under an RC step
and any figures identified in an RC step, must be done to comply
with the AD. If a step or sub-step is labeled ``RC Exempt,'' then
the RC requirement is removed from that step or sub-step. An AMOC is
required for any deviations to RC steps, including substeps and
identified figures.
(ii) Steps not labeled as RC may be deviated from using accepted
methods in accordance with the operator's maintenance or inspection
program without obtaining approval of an AMOC, provided the RC
steps, including substeps and identified figures, can still be done
as specified, and the airplane can be put back in an airworthy
condition.
(n) Related Information
(1) For more information about this AD, contact Payman Soltani,
Aerospace Engineer, Airframe Branch, ANM-120L, FAA, Los Angeles ACO,
3960 Paramount Boulevard, Lakewood, CA 90712-4137; phone: 562-627-
5313; fax: 562-627-5210; email: payman.soltani@faa.gov.
(2) For service information identified in this AD, contact
Boeing Commercial Airplanes, Attention: Contractual & Data Services
(C&DS), 2600 Westminster Blvd., MC 110-SK57, Seal Beach, CA 90740;
telephone 562-797-1717; 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 December 16, 2016.
Ross Landes,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2016-31367 Filed 1-4-17; 8:45 am]
BILLING CODE 4910-13-P
