Airworthiness Directives; The Boeing Company Airplanes, 21716-21720 [2016-08359]
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Federal Register / Vol. 81, No. 71 / Wednesday, April 13, 2016 / Rules and Regulations
Worth, TX 76177; telephone (817) 222–5110;
email 9-ASW-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.
Issued in Fort Worth, Texas, on March 31,
2016.
James A. Grigg,
Acting Manager, Rotorcraft Directorate,
Aircraft Certification Service.
(g) Additional Information
Federal Aviation Administration
(1) Airbus Helicopters Alert Service
Bulletin ASB No. SA341/SA342–05.40,
Revision 0, dated April 28, 2014, which is
not incorporated by reference, contains
additional information about the subject of
this final rule. For Airbus Helicopters service
information identified in this final rule,
contact Airbus Helicopters, 2701 N. Forum
Drive, Grand Prairie, TX 75052; telephone
(972) 641–0000 or (800) 232–0323; fax (972)
641–3775; or at https://
www.airbushelicopters.com/techpub. You
may review a copy of the service information
at the FAA, Office of the Regional Counsel,
Southwest Region, 10101 Hillwood Pkwy,
Room 6N–321, Fort Worth, TX 76177.
(2) The subject of this AD is addressed in
European Aviation Safety Agency (EASA) AD
No. 2014–0216, dated September 24, 2014.
You may view the EASA AD on the Internet
at https://www.regulations.gov in Docket No.
FAA–2015–5914.
(h) Subject
Joint Aircraft Service Component (JASC)
Code: 6700, Main Rotor.
jstallworth on DSK7TPTVN1PROD with RULES
(i) Material Incorporated by Reference
(1) The Director of the Federal Register
approved the incorporation by reference of
the service information listed in this
paragraph under 5 U.S.C. 552(a) and 1 CFR
part 51.
(2) You must use this service information
as applicable to do the actions required by
this AD, unless the AD specifies otherwise.
(i) Gazelle Inspection—Check 65.12.607,
‘‘Main Rotor Head: Torsion Tie-Back Check
(Post MOD 076171),’’ dated August 2008, of
the Eurocopter Gazelle Helicopter
Maintenance Manual, Tome 1.
(ii) Reserved.
(3) For Eurocopter service information
identified in this final rule, contact Airbus
Helicopters, 2701 N. Forum Drive, Grand
Prairie, TX 75052; telephone (972) 641–0000
or (800) 232–0323; fax (972) 641–3775; or at
https://www.airbushelicopters.com/techpub.
(4) You may view this service information
at FAA, Office of the Regional Counsel,
Southwest Region, 10101 Hillwood Pkwy,
Room 6N–321, Fort Worth, TX 76177. For
information on the availability of this
material at the FAA, call (817) 222–5110.
(5) You may view this service information
that is incorporated by reference at the
National Archives and Records
Administration (NARA). For information on
the availability of this material at NARA, call
(202) 741–6030, or go to: https://
www.archives.gov/federal-register/cfr/ibrlocations.html.
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[FR Doc. 2016–07979 Filed 4–12–16; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
14 CFR Part 39
[Docket No. FAA–2015–3147; Directorate
Identifier 2014–NM–094–AD; Amendment
39–18479; AD 2016–08–03]
RIN 2120–AA64
Airworthiness Directives; The Boeing
Company Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule.
AGENCY:
We are adopting a new
airworthiness directive (AD) for all The
Boeing Company Model 777–200,
–200LR, –300, and –300ER series
airplanes. This AD was prompted by
reports of fractured forward attach
fittings of the inboard flap outboard aft
flap track. The fractured fittings were
determined to be the result of corrosion
pits forming on the inside diameter of
the fittings. This AD requires an
inspection for the affected part number
and serial number of the main flap;
various additional repetitive inspections
of the fitting, if necessary; and
replacement of the fitting or nested
bushing installation, if necessary, which
would terminate the inspections. This
AD also provides an optional
terminating action for the repetitive
inspections. We are issuing this AD to
detect and correct fracture of the fitting,
which could result in the loss of the
inboard aft flap and could lead to a
punctured fuselage, causing injury to
the flightcrew and passengers, and
damage to the airplane.
DATES: This AD is effective May 18,
2016.
The Director of the Federal Register
approved the incorporation by reference
of a certain publication listed in this AD
as of May 18, 2016.
ADDRESSES: For service information
identified in this final rule, 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
SUMMARY:
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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–
3147.
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–
3147; 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 AD, the regulatory
evaluation, any comments received, and
other information. The address for the
Docket Office (phone: 800–647–5527) is
Docket Management Facility, U.S.
Department of Transportation, Docket
Operations, M–30, West Building
Ground Floor, Room W12–140, 1200
New Jersey Avenue SE., Washington,
DC 20590.
FOR FURTHER INFORMATION CONTACT: Eric
Lin, Aerospace Engineer, Airframe
Branch, ANM–120S, FAA, Seattle
Aircraft Certification Office, 1601 Lind
Avenue SW., Renton, WA 98057–3356;
telephone: 425–917–6412; fax: 425–
917–6590; email: Eric.Lin@faa.gov.
SUPPLEMENTARY INFORMATION:
Discussion
We issued a notice of proposed
rulemaking (NPRM) to amend 14 CFR
part 39 by adding an AD that would
apply to all The Boeing Company Model
777–200, –200LR, –300, and –300ER
series airplanes. The NPRM published
in the Federal Register on August 25,
2015 (80 FR 51491) (‘‘the NPRM’’). The
NPRM was prompted by reports of
fractured forward attach fittings of the
inboard flap outboard aft flap track. The
fractured fittings were determined to be
the result of corrosion pits forming on
the inside diameter of the fittings. The
NPRM proposed to require an
inspection for the affected part number
and serial number of the main flap;
various additional repetitive inspections
of the fitting, if necessary; and
replacement of the fitting or nested
bushing installation, if necessary, which
would terminate the inspections. The
proposed AD also provided an optional
terminating action for the repetitive
inspections. We are issuing this AD to
detect and correct fracture of the fitting,
which could result in the loss of the
inboard aft flap and could lead to a
punctured fuselage, causing injury to
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the flightcrew and passengers, and
damage to the airplane.
Comments
We gave the public the opportunity to
participate in developing this AD. The
following presents the comments
received on the NPRM and the FAA’s
response to each comment. Benjamin
Kerensa commented that he supports
the NPRM.
jstallworth on DSK7TPTVN1PROD with RULES
Request To Change Terminology
Boeing requested that we change the
phrase ‘‘inboard flap of the main flap’’
to ‘‘main flap of the inboard flap
assembly’’ in paragraphs (g) and (h) of
the proposed AD. Boeing stated that this
would clarify the inspection location.
We agree with the commenter’s
request for the reason provided by the
commenter. We have revised paragraphs
(g) and (h) of this AD accordingly.
Request To Clarify Requirements of a
Certain Terminating Action
Boeing requested that we revise the
terminating action specified in
paragraph (k)(1) of the proposed AD.
Boeing recommended that at the end of
paragraph (k)(1) of the proposed AD, we
add the following language, ‘‘Prior to
accomplishing this option, the
inspections of paragraph (h) must be
accomplished and no cracking must
have been found during that
inspection.’’ Boeing commented that the
bushing replacement is only a
terminating action if the fitting has been
verified to be crack free.
We agree to clarify the terminating
action. As specified in Boeing Special
Attention Service Bulletin 777–57–
0094, Revision 1, dated November 5,
2014, if cracking is found during an
inspection that is part of the terminating
action, a fitting replacement must be
done instead of the terminating action.
In addition, Boeing Special Attention
Service Bulletin 777–57–0094, Revision
1, dated November 5, 2014, specifies
that if corrosion cannot be removed
during the terminating action, a fitting
replacement must be done instead of the
terminating action.
Therefore, we have revised paragraph
(k)(1) of this AD to specify that the
terminating action is acceptable
provided no cracking is found during
any inspection specified in Part 4 of the
Accomplishment Instructions of Boeing
Special Attention Service Bulletin 777–
57–0094, Revision 1, dated November 5,
2014, and all corrosion has been
removed.
We have also clarified the terminating
actions specified in paragraphs (h), (i),
(j), (k)(1), (k)(2), and (k)(3) of this AD to
specify the terminating actions apply
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only to that fitting on which the
terminating action is done.
In addition, we have clarified the
actions specified in paragraphs (i)(3)(i),
(i)(3)(ii), and (i)(3)(iii) of this AD by
specifying the actions include doing all
applicable related investigative actions.
Also, we have clarified the actions
specified in paragraphs (j)(1) and (j)(2)
of this AD by specifying the actions
include doing all applicable related
investigative and corrective actions.
Request To Clarify Terminating Action
Is an Option to the Inspections
Boeing and American Airlines (AA)
requested that we clarify that the
terminating action can be done instead
of the inspections. AA commented to
revise the terminating action paragraph
to state the following:
If any inboard flap of the main flap having
an affected part number and serial number is
found during the inspection required by
paragraph (g) of this AD: Except as provided
by paragraph (l) of this AD, at the applicable
time specified in paragraph 1.E.,
‘‘Compliance,’’ of Boeing Special Attention
Service Bulletin 777–57–0094, Revision 1,
dated November 5, 2014, do the terminating
action in paragraph (k)(1), (k)(2), or (k)(3) of
this AD or do the inspections specified in
paragraph (h)(1) or (h)(2) of this AD, in
accordance with the Accomplishment
Instructions of Boeing Special attention
Service Bulletin 777–57–0094, Revision 1,
dated November 5, 2014. Repeat the
inspections thereafter at the applicable times
specified in paragraph 1.E., ‘‘Compliance,’’ of
Boeing Special Attention Service Bulletin
777–57–0094, Revision 1, dated November 5,
2014, until a terminating action in paragraph
(k)(1), (k)(2), or (k)(3) of this AD is done.
AA commented that this change
would align the proposed rule with
paragraph 1.E., ‘‘Compliance,’’ table 1
and table 2, of Boeing Special Attention
Service Bulletin 777–57–0094, Revision
1, dated November 5, 2014. AA also
stated that this would clearly indicate
that the terminating action would
preclude having to accomplish first the
initial inspection requirement in
paragraph (h) of the proposed AD.
Boeing requested that we add a sentence
to the end of paragraph (h) to specify
that the inspections are not required for
any affected inboard flap assembly
where one of the terminating actions
specified in paragraph (k)(1), (k)(2), or
(k)(3) of the proposed AD have been
done.
We agree with the commenters’
request. We have revised paragraph (h)
of this AD to clarify that the terminating
actions may preclude the initial
inspections because rework or
replacement of the parts prevent the
unsafe condition.
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Request To Clarify the Applicability
Delta Airlines (DAL) requested that
we clarify whether paragraph (c) of the
proposed AD is intended for all Model
777–200, –200LR, –300, and –300ER
series airplanes, or all Model 777–200,
–200LR, –300 and –300ER series
airplanes, identified as Groups 1, 2, and
4 airplanes in Boeing Special Attention
Service Bulletin 777–57–0094, Revision
1, dated November 5, 2014.
DAL stated that paragraph (c) of the
proposed AD does not contain Boeing
Special Attention Service Bulletin 777–
57–0094, Revision 1, dated November 5,
2014, to identify the airplane’s
applicability for the proposed AD. DAL
commented that in the proposed rule
under ‘‘Differences Between This
Proposed AD and the Service
Information,’’ the airplane’s
applicability is stated. DAL also stated
that the same paragraph states that the
proposed AD is applicable only to
Groups 1, 2, and 4 airplanes (Model
777–200, –200LR, –300 and –300ER
series airplanes) specified in Boeing
Service Bulletin 777–57–0094, Revision
1, dated November 5, 2014. DAL
commented that a review of the
‘‘Compliance’’ paragraph in the service
information indicates that the FAA will
possibly release an AD for airplanes in
Groups 1, 2, and 4.
We agree with the commenter’s
request to clarify the applicability of
this AD. This AD applies to all Model
777–200, –200LR, –300, and –300ER
series airplanes as specified in
paragraph (c) of this AD. The
description of Groups 1, 2, and 4
airplanes in section 1.A., ‘‘Effectivity,’’
of Boeing Special Attention Service
Bulletin 777–57–0094, Revision 1, dated
November 5, 2014, specifies Model 777–
200, –200LR, –300, and –300ER series
airplanes. Additionally, as noted in the
service information, the table of variable
numbers given in section 1.A.,
‘‘Effectivity,’’ only reflects up to line
number 1322, and affected airplanes
after line number 1322 will be added to
the profile page of MyBoeingFleet.com.
Therefore, this AD applies to all Model
777–200, –200LR, –300, and –300ER
series airplanes. We have not changed
this AD in this regard.
Conclusion
We reviewed the relevant data,
considered the comments received, and
determined that air safety and the
public interest require adopting this AD
with the changes described previously
and minor editorial changes. We have
determined that these minor changes:
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• Are consistent with the intent that
was proposed in the NPRM for
correcting the unsafe condition; and
• Do not add any additional burden
upon the public than was already
proposed in the NPRM.
We also determined that these
changes will not increase the economic
burden on any operator or increase the
scope of this AD.
Related Service Information Under 1
CFR Part 51
We reviewed Boeing Special
Attention Service Bulletin 777–57–
0094, Revision 1, dated November 5,
2014. The service information describes
procedures for an inspection for the
affected part number and serial number
of the main flap; various additional
repetitive inspections of the fitting, if
necessary; and replacement of the fitting
or nested bushing installation, if
necessary, which would terminate the
inspections. The service information
also describes an optional terminating
action for the repetitive inspections.
This service information is reasonably
available because the interested parties
have access to it through their normal
course of business or by the means
identified in the ADDRESSES section.
Costs of Compliance
We estimate that this AD affects 148
airplanes of U.S. registry.
We estimate the following costs to
comply with this AD:
ESTIMATED COSTS
Action
Labor cost
Inspection to determine the part
number.
Additional Inspections .......................
3 work-hours × $85 per hour = $255
$0
$255 ..............................
$37,740.
Up to 7 work-hours × $85 per hour =
$595, per cycle.
0
Up to $595, per cycle ...
Up to $88,060, per
cycle.
We estimate the following costs to do
any necessary replacements that will be
required based on the results of the
Parts cost
Cost per product
inspection. The nested bushing
installation of the attach fitting and the
fitting replacement are also optional
Cost on U.S. operators
terminating actions. We have no way of
determining the number of aircraft on
which these actions might be done.
ON-CONDITION COSTS
Action
Labor cost
Nested bushing installation of the attach fitting ...........
Fitting replacement ......................................................
40 work-hours × $85 per hour = $3,400 .....................
73 work-hours × $85 per hour = $6,205 .....................
According to the manufacturer, all of
the costs of this AD may be covered
under warranty, thereby reducing the
cost impact on affected individuals. We
do not control warranty coverage for
affected individuals. As a result, we
have included all costs in our cost
estimate.
jstallworth on DSK7TPTVN1PROD with 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
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products identified in this rulemaking
action.
Regulatory Findings
This AD will not have federalism
implications under Executive Order
13132. This AD will not have a
substantial direct effect on the States, on
the relationship between the national
government and the States, or on the
distribution of power and
responsibilities among the various
levels of government.
For the reasons discussed above, I
certify that this AD:
(1) Is not a ‘‘significant regulatory
action’’ under Executive Order 12866,
(2) Is not a ‘‘significant rule’’ under
DOT Regulatory Policies and Procedures
(44 FR 11034, February 26, 1979),
(3) Will not affect intrastate aviation
in Alaska, and
(4) Will not have a significant
economic impact, positive or negative,
on a substantial number of small entities
under the criteria of the Regulatory
Flexibility Act.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation
safety, Incorporation by reference,
Safety.
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Parts cost
Cost per product
$45
7,400
$3,445.
13,605.
Adoption of the Amendment
Accordingly, under the authority
delegated to me by the Administrator,
the FAA amends 14 CFR part 39 as
follows:
PART 39—AIRWORTHINESS
DIRECTIVES
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):
■
2016–08–03 The Boeing Company:
Amendment 39–18479; Docket No.
FAA–2015–3147; Directorate Identifier
2014–NM–094–AD.
(a) Effective Date
This AD is effective May 18, 2016.
(b) Affected ADs
None.
(c) Applicability
This AD applies to all The Boeing
Company Model 777–200, –200LR, –300, and
–300ER series airplanes, certificated in any
category.
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(d) Subject
Air Transport Association (ATA) of
America Code 57, Wings.
(e) Unsafe Condition
This AD was prompted by reports of
fractured forward attach fittings of the
inboard flap outboard aft flap track. The
fractured fittings were determined to be the
result of corrosion pits forming on the inside
diameter of the fittings. We are issuing this
AD to detect and correct fracture of the
fitting, which could result in the loss of the
inboard aft flap and could lead to a
punctured fuselage, causing injury to the
flightcrew and passengers, and damage to the
airplane.
(f) Compliance
Comply with this AD within the
compliance times specified, unless already
done.
jstallworth on DSK7TPTVN1PROD with RULES
(g) Inspection To Determine the Part Number
At the applicable time specified in
paragraph 1.E., ‘‘Compliance,’’ of Boeing
Special Attention Service Bulletin 777–57–
0094, Revision 1, dated November 5, 2014,
except as provided by paragraph (l) of this
AD: Do an inspection of the main flap of the
inboard flap assembly for affected part and
serial numbers, in accordance with the
Accomplishment Instructions of Boeing
Special Attention Service Bulletin 777–57–
0094, Revision 1, dated November 5, 2014. A
review of airplane maintenance records is
acceptable in lieu of this inspection if the
part number and serial number of the inboard
flap can be conclusively determined from
that review.
(h) Additional Inspections
If any main flap of the inboard flap
assembly having an affected part number and
serial number is found during the inspection
required by paragraph (g) of this AD: Except
as provided by paragraph (l) of this AD, at
the applicable time specified in paragraph
1.E., ‘‘Compliance,’’ of Boeing Special
Attention Service Bulletin 777–57–0094,
Revision 1, dated November 5, 2014, do the
terminating action specified in paragraph
(k)(1), (k)(2), or (k)(3) of this AD, or do the
inspections specified in paragraph (h)(1) or
(h)(2) of this AD, in accordance with the
Accomplishment Instructions of Boeing
Special Attention Service Bulletin 777–57–
0094, Revision 1, dated November 5, 2014.
Repeat the inspections thereafter at the
applicable times specified in paragraph 1.E.,
‘‘Compliance,’’ of Boeing Special Attention
Service Bulletin 777–57–0094, Revision 1,
dated November 5, 2014, until a terminating
action in paragraph (k)(1), (k)(2), or (k)(3) of
this AD is done. Accomplishing a
terminating action specified in paragraph
(k)(1), (k)(2), or (k)(3) of this AD terminates
the inspections required by this paragraph for
that fitting only.
(1) At the forward attach fitting of the aft
flap track of the inboard flap: Do a detailed
inspection for cracking and bushing
migration, and a high frequency eddy current
inspection for cracking, in accordance with
Part 2 of the Accomplishment Instructions of
Boeing Special Attention Service Bulletin
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777–57–0094, Revision 1, dated November 5,
2014.
(2) At the forward attach fitting of the aft
flap track of the inboard flap: Do a detailed
inspection for cracking and bushing
migration, and an ultrasound inspection for
cracking, in accordance with Part 3 of the
Accomplishment Instructions of Boeing
Special Attention Service Bulletin 777–57–
0094, Revision 1, dated November 5, 2014.
(i) Corrective Action for Bushing Migration
If any bushing migration but no cracking is
found during any inspection required by
paragraph (h) of this AD: At the applicable
times specified in paragraph 1.E.,
‘‘Compliance,’’ of Boeing Special Attention
Service Bulletin 777–57–0094, Revision 1,
dated November 5, 2014, do the actions
specified in paragraphs (i)(1) through (i)(3) of
this AD. Accomplishment of a terminating
action specified in paragraph (i)(3) or (k) of
this AD terminates the actions required by
this paragraph for that fitting only.
(1) Apply corrosion inhibiting compound
BMS 3–23, Type II, around the bushing
flanges on each side of the fitting, in
accordance with the Accomplishment
Instructions of Boeing Special Attention
Service Bulletin 777–57–0094, Revision 1,
dated November 5, 2014. Re-apply the
corrosion inhibiting compound at the time
specified in paragraph 1.E., ‘‘Compliance,’’ of
Boeing Special Attention Service Bulletin
777–57–0094, Revision 1, dated November 5,
2014.
(2) Repeat the inspections specified in
paragraph (h)(1) or (h)(2) of this AD, except
inspect for cracking only.
(3) Do a terminating action specified in
paragraph (i)(3)(i), (i)(3)(ii), or (i)(3)(iii) of
this AD.
(i) Install a nested bushing to the forward
attach fitting of the aft flap track of the
inboard flap, including doing all applicable
related investigative actions, in accordance
with Part 4 of the Accomplishment
Instructions of Boeing Special Attention
Service Bulletin 777–57–0094, Revision 1,
dated November 5, 2014.
(ii) Replace the forward attach fitting of the
aft flap track of the inboard flap with an
aluminum fitting, including doing all
applicable related investigative actions, in
accordance with Part 5 of the
Accomplishment Instructions of Boeing
Special Attention Service Bulletin 777–57–
0094, Revision 1, dated November 5, 2014.
(iii) Replace the forward attach fitting of
the aft flap track of the inboard flap with a
titanium fitting, including doing all
applicable related investigative actions, in
accordance with Part 6 of the
Accomplishment Instructions of Boeing
Special Attention Service Bulletin 777–57–
0094, Revision 1, dated November 5, 2014.
(j) Corrective Actions for Cracking
If any cracking is found during any
inspection required by paragraph (h) or (i)(3)
of this AD: At the applicable time specified
in paragraph 1.E., ‘‘Compliance,’’ of Boeing
Special Attention Service Bulletin 777–57–
0094, Revision 1, dated November 5, 2014,
do a terminating action specified in
paragraph (j)(1) or (j)(2) of this AD.
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21719
Replacement of the forward attach fitting as
specified in paragraph (j)(1) or (j)(2) of this
AD terminates the actions in this AD for that
fitting only.
(1) Replace the forward attach fitting of the
aft flap track of the inboard flap with an
aluminum fitting, including doing all
applicable related investigative and
corrective actions, in accordance with Part 5
of the Accomplishment Instructions of
Boeing Special Attention Service Bulletin
777–57–0094, Revision 1, dated November 5,
2014.
(2) Replace the forward attach fitting of the
aft flap track of the inboard flap with a
titanium fitting, including doing all
applicable related investigative and
corrective actions, in accordance with Part 6
of the Accomplishment Instructions of
Boeing Special Attention Service Bulletin
777–57–0094, Revision 1, dated November 5,
2014.
(k) Optional Terminating Actions
(1) Installation of the nested bushing to the
forward attach fitting of the aft flap track of
the inboard flap, in accordance with Part 4
of the Accomplishment Instructions of
Boeing Special Attention Service Bulletin
777–57–0094, Revision 1, dated November 5,
2014, terminates the requirements of this AD
for that fitting only, provided no cracking is
found during any inspection specified in Part
4 of the Accomplishment Instructions of
Boeing Special Attention Service Bulletin
777–57–0094, Revision 1, dated November 5,
2014, and all corrosion has been removed.
(2) Replacement of the forward attach
fitting of the aft flap track of the inboard flap
with an aluminum fitting, in accordance with
Part 5 of the Accomplishment Instructions of
Boeing Special Attention Service Bulletin
777–57–0094, Revision 1, dated November 5,
2014, terminates the requirements of this AD
for that fitting only.
(3) Replacement of the forward attach
fitting of the aft flap track of the inboard flap
with a titanium fitting, in accordance with
Part 6 of the Accomplishment Instructions of
Boeing Special Attention Service Bulletin
777–57–0094, Revision 1, dated November 5,
2014, terminates the requirements of this AD
for that fitting only.
(l) Exception to the Service Information
Where Boeing Special Attention Service
Bulletin 777–57–0094, Revision 1, dated
November 5, 2014, specifies a compliance
time ‘‘after the original issue date of this
service bulletin,’’ this AD requires
compliance within the specified compliance
time after the effective date of this AD.
(m) Credit for Previous Actions
(1) This paragraph provides credit for the
actions specified in paragraphs (h)(1) and
(h)(2) of this AD, if those actions were
performed before the effective date of this AD
using Boeing Special Attention Service
Bulletin 777–57–0094, dated January 29,
2014, which is not incorporated by reference
in this AD.
(2) This paragraph provides credit for the
actions specified in paragraph (h)(1) of this
AD, if those actions were performed before
the effective date of this AD using Boeing
Multi Operator Message MOM–MOM–13–
E:\FR\FM\13APR1.SGM
13APR1
21720
Federal Register / Vol. 81, No. 71 / Wednesday, April 13, 2016 / Rules and Regulations
0137–01B, dated February 21, 2013, which is
not incorporated by reference in this AD.
(n) 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 (o)(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.
(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) For service information that contains
steps that are labeled as Required for
Compliance (RC), the provisions of
paragraphs (n)(4)(i) and (n)(4)(ii) 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. 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.
(o) Related Information
(1) For more information about this AD,
contact Eric Lin, Aerospace Engineer,
Airframe Branch, ANM–120S, FAA, Seattle
ACO, 1601 Lind Avenue SW., Renton, WA
98057–3356; telephone: 425–917–6412; fax:
425–917–6590; email: Eric.Lin@faa.gov.
(2) Service information identified in this
AD that is not incorporated by reference is
available at the addresses specified in
paragraphs (p)(3) and (p)(4) of this AD.
jstallworth on DSK7TPTVN1PROD with RULES
(p) Material Incorporated by Reference
(1) The Director of the Federal Register
approved the incorporation by reference
(IBR) of the service information listed in this
paragraph under 5 U.S.C. 552(a) and 1 CFR
part 51.
(2) You must use this service information
as applicable to do the actions required by
this AD, unless the AD specifies otherwise.
VerDate Sep<11>2014
14:03 Apr 12, 2016
Jkt 238001
(i) Boeing Special Attention Service
Bulletin 777–57–0094, Revision 1, dated
November 5, 2014.
(ii) Reserved.
(3) For Boeing 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.
(4) You may view this 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.
(5) You may view this service information
that is incorporated by reference at the
National Archives and Records
Administration (NARA). For information on
the availability of this material at NARA, call
202–741–6030, or go to: https://www.archives.
gov/federal-register/cfr/ibr-locations.html.
Issued in Renton, Washington, on March
31, 2016.
Victor Wicklund,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. 2016–08359 Filed 4–12–16; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2015–2959; Directorate
Identifier 2015–NM–008–AD; Amendment
39–18470; AD 2016–07–25]
RIN 2120–AA64
Airworthiness Directives; The Boeing
Company Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule.
AGENCY:
We are adopting a new
airworthiness directive (AD) for certain
The Boeing Company Model 787–8
airplanes. This AD was prompted by
reports indicating that the ram air
turbine (RAT) assembly may fail to
operate if deployed at low airspeeds.
This AD requires replacing either the
RAT pump and control module
assembly or the entire RAT assembly.
We are issuing this AD to prevent
failure of the RAT assembly to operate
at low air speeds. The volume fuse on
the RAT assembly may be activated inflight before the RAT is deployed. This
may lead to improper pump hydraulic
pressure offloading when the RAT is
needed. Failure of the RAT to operate in
an all engine out event would result in
loss of control of the airplane.
SUMMARY:
PO 00000
Frm 00022
Fmt 4700
Sfmt 4700
This AD is effective May 18,
2016.
The Director of the Federal Register
approved the incorporation by reference
of a certain publication listed in this AD
as of May 18, 2016.
ADDRESSES: For service information
identified in this final rule, 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–
2959.
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–
2959; 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 AD, the regulatory
evaluation, any comments received, and
other information. The address for the
Docket Office (phone: 800–647–5527) is
Docket Management Facility, U.S.
Department of Transportation, Docket
Operations, M–30, West Building
Ground Floor, Room W12–140, 1200
New Jersey Avenue SE., Washington,
DC 20590.
FOR FURTHER INFORMATION CONTACT:
Sean J. Schauer, Aerospace Engineer,
Systems and Equipment Branch, ANM–
130S, FAA, Seattle Aircraft Certification
Office (ACO), 1601 Lind Avenue SW.,
Renton, WA 98057–3356; phone: 425–
917–6479; fax: 425–917–6590; email:
sean.schauer@faa.gov.
SUPPLEMENTARY INFORMATION:
Discussion
We issued a notice of proposed
rulemaking (NPRM) to amend 14 CFR
part 39 by adding an AD that would
apply to certain The Boeing Company
Model 787–8 airplanes. The NPRM
published in the Federal Register on
July 24, 2015 (80 FR 43972) (‘‘the
NPRM’’). The NPRM was prompted by
reports indicating that the RAT
assembly may fail to operate if deployed
at low airspeeds. The NPRM proposed
to require replacing either the RAT
pump and control module assembly or
E:\FR\FM\13APR1.SGM
13APR1
]]>Agencies
[Federal Register Volume 81, Number 71 (Wednesday, April 13, 2016)]
[Rules and Regulations]
[Pages 21716-21720]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2016-08359]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2015-3147; Directorate Identifier 2014-NM-094-AD;
Amendment 39-18479; AD 2016-08-03]
RIN 2120-AA64
Airworthiness Directives; The Boeing Company Airplanes
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Final rule.
-----------------------------------------------------------------------
SUMMARY: We are adopting a new airworthiness directive (AD) for all The
Boeing Company Model 777-200, -200LR, -300, and -300ER series
airplanes. This AD was prompted by reports of fractured forward attach
fittings of the inboard flap outboard aft flap track. The fractured
fittings were determined to be the result of corrosion pits forming on
the inside diameter of the fittings. This AD requires an inspection for
the affected part number and serial number of the main flap; various
additional repetitive inspections of the fitting, if necessary; and
replacement of the fitting or nested bushing installation, if
necessary, which would terminate the inspections. This AD also provides
an optional terminating action for the repetitive inspections. We are
issuing this AD to detect and correct fracture of the fitting, which
could result in the loss of the inboard aft flap and could lead to a
punctured fuselage, causing injury to the flightcrew and passengers,
and damage to the airplane.
DATES: This AD is effective May 18, 2016.
The Director of the Federal Register approved the incorporation by
reference of a certain publication listed in this AD as of May 18,
2016.
ADDRESSES: For service information identified in this final rule,
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-
3147.
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-
3147; 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 AD, the regulatory evaluation, any comments received, and
other information. The address for the Docket Office (phone: 800-647-
5527) is Docket Management Facility, U.S. Department of Transportation,
Docket Operations, M-30, West Building Ground Floor, Room W12-140, 1200
New Jersey Avenue SE., Washington, DC 20590.
FOR FURTHER INFORMATION CONTACT: Eric Lin, Aerospace Engineer, Airframe
Branch, ANM-120S, FAA, Seattle Aircraft Certification Office, 1601 Lind
Avenue SW., Renton, WA 98057-3356; telephone: 425-917-6412; fax: 425-
917-6590; email: Eric.Lin@faa.gov.
SUPPLEMENTARY INFORMATION:
Discussion
We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR
part 39 by adding an AD that would apply to all The Boeing Company
Model 777-200, -200LR, -300, and -300ER series airplanes. The NPRM
published in the Federal Register on August 25, 2015 (80 FR 51491)
(``the NPRM''). The NPRM was prompted by reports of fractured forward
attach fittings of the inboard flap outboard aft flap track. The
fractured fittings were determined to be the result of corrosion pits
forming on the inside diameter of the fittings. The NPRM proposed to
require an inspection for the affected part number and serial number of
the main flap; various additional repetitive inspections of the
fitting, if necessary; and replacement of the fitting or nested bushing
installation, if necessary, which would terminate the inspections. The
proposed AD also provided an optional terminating action for the
repetitive inspections. We are issuing this AD to detect and correct
fracture of the fitting, which could result in the loss of the inboard
aft flap and could lead to a punctured fuselage, causing injury to
[[Page 21717]]
the flightcrew and passengers, and damage to the airplane.
Comments
We gave the public the opportunity to participate in developing
this AD. The following presents the comments received on the NPRM and
the FAA's response to each comment. Benjamin Kerensa commented that he
supports the NPRM.
Request To Change Terminology
Boeing requested that we change the phrase ``inboard flap of the
main flap'' to ``main flap of the inboard flap assembly'' in paragraphs
(g) and (h) of the proposed AD. Boeing stated that this would clarify
the inspection location.
We agree with the commenter's request for the reason provided by
the commenter. We have revised paragraphs (g) and (h) of this AD
accordingly.
Request To Clarify Requirements of a Certain Terminating Action
Boeing requested that we revise the terminating action specified in
paragraph (k)(1) of the proposed AD. Boeing recommended that at the end
of paragraph (k)(1) of the proposed AD, we add the following language,
``Prior to accomplishing this option, the inspections of paragraph (h)
must be accomplished and no cracking must have been found during that
inspection.'' Boeing commented that the bushing replacement is only a
terminating action if the fitting has been verified to be crack free.
We agree to clarify the terminating action. As specified in Boeing
Special Attention Service Bulletin 777-57-0094, Revision 1, dated
November 5, 2014, if cracking is found during an inspection that is
part of the terminating action, a fitting replacement must be done
instead of the terminating action. In addition, Boeing Special
Attention Service Bulletin 777-57-0094, Revision 1, dated November 5,
2014, specifies that if corrosion cannot be removed during the
terminating action, a fitting replacement must be done instead of the
terminating action.
Therefore, we have revised paragraph (k)(1) of this AD to specify
that the terminating action is acceptable provided no cracking is found
during any inspection specified in Part 4 of the Accomplishment
Instructions of Boeing Special Attention Service Bulletin 777-57-0094,
Revision 1, dated November 5, 2014, and all corrosion has been removed.
We have also clarified the terminating actions specified in
paragraphs (h), (i), (j), (k)(1), (k)(2), and (k)(3) of this AD to
specify the terminating actions apply only to that fitting on which the
terminating action is done.
In addition, we have clarified the actions specified in paragraphs
(i)(3)(i), (i)(3)(ii), and (i)(3)(iii) of this AD by specifying the
actions include doing all applicable related investigative actions.
Also, we have clarified the actions specified in paragraphs (j)(1) and
(j)(2) of this AD by specifying the actions include doing all
applicable related investigative and corrective actions.
Request To Clarify Terminating Action Is an Option to the Inspections
Boeing and American Airlines (AA) requested that we clarify that
the terminating action can be done instead of the inspections. AA
commented to revise the terminating action paragraph to state the
following:
If any inboard flap of the main flap having an affected part
number and serial number is found during the inspection required by
paragraph (g) of this AD: Except as provided by paragraph (l) of
this AD, at the applicable time specified in paragraph 1.E.,
``Compliance,'' of Boeing Special Attention Service Bulletin 777-57-
0094, Revision 1, dated November 5, 2014, do the terminating action
in paragraph (k)(1), (k)(2), or (k)(3) of this AD or do the
inspections specified in paragraph (h)(1) or (h)(2) of this AD, in
accordance with the Accomplishment Instructions of Boeing Special
attention Service Bulletin 777-57-0094, Revision 1, dated November
5, 2014. Repeat the inspections thereafter at the applicable times
specified in paragraph 1.E., ``Compliance,'' of Boeing Special
Attention Service Bulletin 777-57-0094, Revision 1, dated November
5, 2014, until a terminating action in paragraph (k)(1), (k)(2), or
(k)(3) of this AD is done.
AA commented that this change would align the proposed rule with
paragraph 1.E., ``Compliance,'' table 1 and table 2, of Boeing Special
Attention Service Bulletin 777-57-0094, Revision 1, dated November 5,
2014. AA also stated that this would clearly indicate that the
terminating action would preclude having to accomplish first the
initial inspection requirement in paragraph (h) of the proposed AD.
Boeing requested that we add a sentence to the end of paragraph (h) to
specify that the inspections are not required for any affected inboard
flap assembly where one of the terminating actions specified in
paragraph (k)(1), (k)(2), or (k)(3) of the proposed AD have been done.
We agree with the commenters' request. We have revised paragraph
(h) of this AD to clarify that the terminating actions may preclude the
initial inspections because rework or replacement of the parts prevent
the unsafe condition.
Request To Clarify the Applicability
Delta Airlines (DAL) requested that we clarify whether paragraph
(c) of the proposed AD is intended for all Model 777-200, -200LR, -300,
and -300ER series airplanes, or all Model 777-200, -200LR, -300 and -
300ER series airplanes, identified as Groups 1, 2, and 4 airplanes in
Boeing Special Attention Service Bulletin 777-57-0094, Revision 1,
dated November 5, 2014.
DAL stated that paragraph (c) of the proposed AD does not contain
Boeing Special Attention Service Bulletin 777-57-0094, Revision 1,
dated November 5, 2014, to identify the airplane's applicability for
the proposed AD. DAL commented that in the proposed rule under
``Differences Between This Proposed AD and the Service Information,''
the airplane's applicability is stated. DAL also stated that the same
paragraph states that the proposed AD is applicable only to Groups 1,
2, and 4 airplanes (Model 777-200, -200LR, -300 and -300ER series
airplanes) specified in Boeing Service Bulletin 777-57-0094, Revision
1, dated November 5, 2014. DAL commented that a review of the
``Compliance'' paragraph in the service information indicates that the
FAA will possibly release an AD for airplanes in Groups 1, 2, and 4.
We agree with the commenter's request to clarify the applicability
of this AD. This AD applies to all Model 777-200, -200LR, -300, and -
300ER series airplanes as specified in paragraph (c) of this AD. The
description of Groups 1, 2, and 4 airplanes in section 1.A.,
``Effectivity,'' of Boeing Special Attention Service Bulletin 777-57-
0094, Revision 1, dated November 5, 2014, specifies Model 777-200, -
200LR, -300, and -300ER series airplanes. Additionally, as noted in the
service information, the table of variable numbers given in section
1.A., ``Effectivity,'' only reflects up to line number 1322, and
affected airplanes after line number 1322 will be added to the profile
page of MyBoeingFleet.com. Therefore, this AD applies to all Model 777-
200, -200LR, -300, and -300ER series airplanes. We have not changed
this AD in this regard.
Conclusion
We reviewed the relevant data, considered the comments received,
and determined that air safety and the public interest require adopting
this AD with the changes described previously and minor editorial
changes. We have determined that these minor changes:
[[Page 21718]]
Are consistent with the intent that was proposed in the
NPRM for correcting the unsafe condition; and
Do not add any additional burden upon the public than was
already proposed in the NPRM.
We also determined that these changes will not increase the
economic burden on any operator or increase the scope of this AD.
Related Service Information Under 1 CFR Part 51
We reviewed Boeing Special Attention Service Bulletin 777-57-0094,
Revision 1, dated November 5, 2014. The service information describes
procedures for an inspection for the affected part number and serial
number of the main flap; various additional repetitive inspections of
the fitting, if necessary; and replacement of the fitting or nested
bushing installation, if necessary, which would terminate the
inspections. The service information also describes an optional
terminating action for the repetitive inspections. This service
information is reasonably available because the interested parties have
access to it through their normal course of business or by the means
identified in the ADDRESSES section.
Costs of Compliance
We estimate that this AD affects 148 airplanes of U.S. registry.
We estimate the following costs to comply with this AD:
Estimated Costs
----------------------------------------------------------------------------------------------------------------
Cost on U.S.
Action Labor cost Parts cost Cost per product operators
----------------------------------------------------------------------------------------------------------------
Inspection to determine the part 3 work-hours x $85 $0 $255................ $37,740.
number. per hour = $255.
Additional Inspections........... Up to 7 0 Up to $595, per Up to $88,060, per
work[dash]hours x cycle. cycle.
$85 per hour =
$595, per cycle.
----------------------------------------------------------------------------------------------------------------
We estimate the following costs to do any necessary replacements
that will be required based on the results of the inspection. The
nested bushing installation of the attach fitting and the fitting
replacement are also optional terminating actions. We have no way of
determining the number of aircraft on which these actions might be
done.
On-Condition Costs
----------------------------------------------------------------------------------------------------------------
Action Labor cost Parts cost Cost per product
----------------------------------------------------------------------------------------------------------------
Nested bushing installation of the attach 40 work-hours x $85 per hour = $45 $3,445.
fitting. $3,400.
Fitting replacement........................... 73 work-hours x $85 per hour = 7,400 13,605.
$6,205.
----------------------------------------------------------------------------------------------------------------
According to the manufacturer, all of the costs of this AD may be
covered under warranty, thereby reducing the cost impact on affected
individuals. We do not control warranty coverage for affected
individuals. As a result, we have included all costs in our cost
estimate.
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
This AD will not have federalism implications under Executive Order
13132. This AD will not have a substantial direct effect on the States,
on the relationship between the national government and the States, or
on the distribution of power and responsibilities among the various
levels of government.
For the reasons discussed above, I certify that this AD:
(1) Is not a ``significant regulatory action'' under Executive
Order 12866,
(2) Is not a ``significant rule'' under DOT Regulatory Policies and
Procedures (44 FR 11034, February 26, 1979),
(3) Will not affect intrastate aviation in Alaska, and
(4) Will not have a significant economic impact, positive or
negative, on a substantial number of small entities under the criteria
of the Regulatory Flexibility Act.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.
Adoption of the Amendment
Accordingly, under the authority delegated to me by the
Administrator, the FAA amends 14 CFR part 39 as follows:
PART 39--AIRWORTHINESS DIRECTIVES
0
1. The authority citation for part 39 continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
Sec. 39.13 [Amended]
0
2. The FAA amends Sec. 39.13 by adding the following new airworthiness
directive (AD):
2016-08-03 The Boeing Company: Amendment 39-18479; Docket No. FAA-
2015-3147; Directorate Identifier 2014-NM-094-AD.
(a) Effective Date
This AD is effective May 18, 2016.
(b) Affected ADs
None.
(c) Applicability
This AD applies to all The Boeing Company Model 777-200, -200LR,
-300, and -300ER series airplanes, certificated in any category.
[[Page 21719]]
(d) Subject
Air Transport Association (ATA) of America Code 57, Wings.
(e) Unsafe Condition
This AD was prompted by reports of fractured forward attach
fittings of the inboard flap outboard aft flap track. The fractured
fittings were determined to be the result of corrosion pits forming
on the inside diameter of the fittings. We are issuing this AD to
detect and correct fracture of the fitting, which could result in
the loss of the inboard aft flap and could lead to a punctured
fuselage, causing injury to the flightcrew and passengers, and
damage to the airplane.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(g) Inspection To Determine the Part Number
At the applicable time specified in paragraph 1.E.,
``Compliance,'' of Boeing Special Attention Service Bulletin 777-57-
0094, Revision 1, dated November 5, 2014, except as provided by
paragraph (l) of this AD: Do an inspection of the main flap of the
inboard flap assembly for affected part and serial numbers, in
accordance with the Accomplishment Instructions of Boeing Special
Attention Service Bulletin 777-57-0094, Revision 1, dated November
5, 2014. A review of airplane maintenance records is acceptable in
lieu of this inspection if the part number and serial number of the
inboard flap can be conclusively determined from that review.
(h) Additional Inspections
If any main flap of the inboard flap assembly having an affected
part number and serial number is found during the inspection
required by paragraph (g) of this AD: Except as provided by
paragraph (l) of this AD, at the applicable time specified in
paragraph 1.E., ``Compliance,'' of Boeing Special Attention Service
Bulletin 777-57-0094, Revision 1, dated November 5, 2014, do the
terminating action specified in paragraph (k)(1), (k)(2), or (k)(3)
of this AD, or do the inspections specified in paragraph (h)(1) or
(h)(2) of this AD, in accordance with the Accomplishment
Instructions of Boeing Special Attention Service Bulletin 777-57-
0094, Revision 1, dated November 5, 2014. Repeat the inspections
thereafter at the applicable times specified in paragraph 1.E.,
``Compliance,'' of Boeing Special Attention Service Bulletin 777-57-
0094, Revision 1, dated November 5, 2014, until a terminating action
in paragraph (k)(1), (k)(2), or (k)(3) of this AD is done.
Accomplishing a terminating action specified in paragraph (k)(1),
(k)(2), or (k)(3) of this AD terminates the inspections required by
this paragraph for that fitting only.
(1) At the forward attach fitting of the aft flap track of the
inboard flap: Do a detailed inspection for cracking and bushing
migration, and a high frequency eddy current inspection for
cracking, in accordance with Part 2 of the Accomplishment
Instructions of Boeing Special Attention Service Bulletin 777-57-
0094, Revision 1, dated November 5, 2014.
(2) At the forward attach fitting of the aft flap track of the
inboard flap: Do a detailed inspection for cracking and bushing
migration, and an ultrasound inspection for cracking, in accordance
with Part 3 of the Accomplishment Instructions of Boeing Special
Attention Service Bulletin 777-57-0094, Revision 1, dated November
5, 2014.
(i) Corrective Action for Bushing Migration
If any bushing migration but no cracking is found during any
inspection required by paragraph (h) of this AD: At the applicable
times specified in paragraph 1.E., ``Compliance,'' of Boeing Special
Attention Service Bulletin 777-57-0094, Revision 1, dated November
5, 2014, do the actions specified in paragraphs (i)(1) through
(i)(3) of this AD. Accomplishment of a terminating action specified
in paragraph (i)(3) or (k) of this AD terminates the actions
required by this paragraph for that fitting only.
(1) Apply corrosion inhibiting compound BMS 3-23, Type II,
around the bushing flanges on each side of the fitting, in
accordance with the Accomplishment Instructions of Boeing Special
Attention Service Bulletin 777-57-0094, Revision 1, dated November
5, 2014. Re-apply the corrosion inhibiting compound at the time
specified in paragraph 1.E., ``Compliance,'' of Boeing Special
Attention Service Bulletin 777-57-0094, Revision 1, dated November
5, 2014.
(2) Repeat the inspections specified in paragraph (h)(1) or
(h)(2) of this AD, except inspect for cracking only.
(3) Do a terminating action specified in paragraph (i)(3)(i),
(i)(3)(ii), or (i)(3)(iii) of this AD.
(i) Install a nested bushing to the forward attach fitting of
the aft flap track of the inboard flap, including doing all
applicable related investigative actions, in accordance with Part 4
of the Accomplishment Instructions of Boeing Special Attention
Service Bulletin 777-57-0094, Revision 1, dated November 5, 2014.
(ii) Replace the forward attach fitting of the aft flap track of
the inboard flap with an aluminum fitting, including doing all
applicable related investigative actions, in accordance with Part 5
of the Accomplishment Instructions of Boeing Special Attention
Service Bulletin 777-57-0094, Revision 1, dated November 5, 2014.
(iii) Replace the forward attach fitting of the aft flap track
of the inboard flap with a titanium fitting, including doing all
applicable related investigative actions, in accordance with Part 6
of the Accomplishment Instructions of Boeing Special Attention
Service Bulletin 777-57-0094, Revision 1, dated November 5, 2014.
(j) Corrective Actions for Cracking
If any cracking is found during any inspection required by
paragraph (h) or (i)(3) of this AD: At the applicable time specified
in paragraph 1.E., ``Compliance,'' of Boeing Special Attention
Service Bulletin 777-57-0094, Revision 1, dated November 5, 2014, do
a terminating action specified in paragraph (j)(1) or (j)(2) of this
AD. Replacement of the forward attach fitting as specified in
paragraph (j)(1) or (j)(2) of this AD terminates the actions in this
AD for that fitting only.
(1) Replace the forward attach fitting of the aft flap track of
the inboard flap with an aluminum fitting, including doing all
applicable related investigative and corrective actions, in
accordance with Part 5 of the Accomplishment Instructions of Boeing
Special Attention Service Bulletin 777-57-0094, Revision 1, dated
November 5, 2014.
(2) Replace the forward attach fitting of the aft flap track of
the inboard flap with a titanium fitting, including doing all
applicable related investigative and corrective actions, in
accordance with Part 6 of the Accomplishment Instructions of Boeing
Special Attention Service Bulletin 777-57-0094, Revision 1, dated
November 5, 2014.
(k) Optional Terminating Actions
(1) Installation of the nested bushing to the forward attach
fitting of the aft flap track of the inboard flap, in accordance
with Part 4 of the Accomplishment Instructions of Boeing Special
Attention Service Bulletin 777-57-0094, Revision 1, dated November
5, 2014, terminates the requirements of this AD for that fitting
only, provided no cracking is found during any inspection specified
in Part 4 of the Accomplishment Instructions of Boeing Special
Attention Service Bulletin 777-57-0094, Revision 1, dated November
5, 2014, and all corrosion has been removed.
(2) Replacement of the forward attach fitting of the aft flap
track of the inboard flap with an aluminum fitting, in accordance
with Part 5 of the Accomplishment Instructions of Boeing Special
Attention Service Bulletin 777-57-0094, Revision 1, dated November
5, 2014, terminates the requirements of this AD for that fitting
only.
(3) Replacement of the forward attach fitting of the aft flap
track of the inboard flap with a titanium fitting, in accordance
with Part 6 of the Accomplishment Instructions of Boeing Special
Attention Service Bulletin 777-57-0094, Revision 1, dated November
5, 2014, terminates the requirements of this AD for that fitting
only.
(l) Exception to the Service Information
Where Boeing Special Attention Service Bulletin 777-57-0094,
Revision 1, dated November 5, 2014, specifies a compliance time
``after the original issue date of this service bulletin,'' this AD
requires compliance within the specified compliance time after the
effective date of this AD.
(m) Credit for Previous Actions
(1) This paragraph provides credit for the actions specified in
paragraphs (h)(1) and (h)(2) of this AD, if those actions were
performed before the effective date of this AD using Boeing Special
Attention Service Bulletin 777-57-0094, dated January 29, 2014,
which is not incorporated by reference in this AD.
(2) This paragraph provides credit for the actions specified in
paragraph (h)(1) of this AD, if those actions were performed before
the effective date of this AD using Boeing Multi Operator Message
MOM-MOM-13-
[[Page 21720]]
0137-01B, dated February 21, 2013, which is not incorporated by
reference in this AD.
(n) 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 (o)(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.
(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) For service information that contains steps that are labeled
as Required for Compliance (RC), the provisions of paragraphs
(n)(4)(i) and (n)(4)(ii) 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. 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.
(o) Related Information
(1) For more information about this AD, contact Eric Lin,
Aerospace Engineer, Airframe Branch, ANM-120S, FAA, Seattle ACO,
1601 Lind Avenue SW., Renton, WA 98057-3356; telephone: 425-917-
6412; fax: 425-917-6590; email: Eric.Lin@faa.gov.
(2) Service information identified in this AD that is not
incorporated by reference is available at the addresses specified in
paragraphs (p)(3) and (p)(4) of this AD.
(p) Material Incorporated by Reference
(1) The Director of the Federal Register approved the
incorporation by reference (IBR) of the service information listed
in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51.
(2) You must use this service information as applicable to do
the actions required by this AD, unless the AD specifies otherwise.
(i) Boeing Special Attention Service Bulletin 777-57-0094,
Revision 1, dated November 5, 2014.
(ii) Reserved.
(3) For Boeing 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.
(4) You may view this 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.
(5) You may view this service information that is incorporated
by reference at the National Archives and Records Administration
(NARA). For information on the availability of this material at
NARA, call 202-741-6030, or go to: https://www.archives.gov/federal-register/cfr/ibr-locations.html.
Issued in Renton, Washington, on March 31, 2016.
Victor Wicklund,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2016-08359 Filed 4-12-16; 8:45 am]
BILLING CODE 4910-13-P
