80 FR 65616 - Airworthiness Directives; The Boeing Company Airplanes

DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration

Federal Register Volume 80, Issue 207 (October 27, 2015)

Page Range		65616-65618
FR Document		2015-26979

We are superseding Airworthiness Directive (AD) 2007-16-08, which applied to all The Boeing Company Model 747-100, 747-100B, 747- 100B SUD, 747-200B, 747-200C, 747-300, 747-400, 747-400D, and 747SR series airplanes. AD 2007-16-08 required repetitive inspections for cracking of the station 800 frame assembly, and repair if necessary. This new AD continues to require repetitive inspections for cracking of the station 800 frame assembly, and repair if necessary, and expands the inspection area. This AD was prompted by reports of cracks found at the forward and aft inner chord strap and angles on the station 800 frame on the left-side and right-side main entry doors. We are issuing this AD to detect and correct fatigue cracks that could extend and fully sever the frame, which could result in development of skin cracks that could lead to rapid depressurization of the airplane.

Federal Register, Volume 80 Issue 207 (Tuesday, October 27, 2015)

[Federal Register Volume 80, Number 207 (Tuesday, October 27, 2015)]
[Rules and Regulations]
[Pages 65616-65618]
From the Federal Register Online [www.thefederalregister.org]
[FR Doc No: 2015-26979]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2015-0498; Directorate Identifier 2014-NM-152-AD;
Amendment 39-18305; AD 2015-22-01]
RIN 2120-AA64

Airworthiness Directives; The Boeing Company Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule.

-----------------------------------------------------------------------

SUMMARY: We are superseding Airworthiness Directive (AD) 2007-16-08,
which applied to all The Boeing Company Model 747-100, 747-100B, 747-
100B SUD, 747-200B, 747-200C, 747-300, 747-400, 747-400D, and 747SR
series airplanes. AD 2007-16-08 required repetitive inspections for
cracking of the station 800 frame assembly, and repair if necessary.
This new AD continues to require repetitive inspections for cracking of
the station 800 frame assembly, and repair if necessary, and expands
the inspection area. This AD was prompted by reports of cracks found at
the forward and aft inner chord strap and angles on the station 800
frame on the left-side and right-side main entry doors. We are issuing
this AD to detect and correct fatigue cracks that could extend and
fully sever the frame, which could result in development of skin cracks
that could lead to rapid depressurization of the airplane.

DATES: This AD is effective December 1, 2015.
The Director of the Federal Register approved the incorporation by
reference of a certain publication listed in this AD as of December 1,
2015.

ADDRESSES: For service information identified in this AD, contact
Boeing Commercial Airplanes, Attention: Data & Services Management,
P.O. Box 3707, MC 2H-65, Seattle, WA 98124-2207; telephone 206-544-
5000, extension 1; fax 206-766-5680; Internet https://www.myboeingfleet.com. You may view this referenced service information
at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW.,
Renton, WA. For information on the availability of this material at the
FAA, call 425-227-1221. It is also available on the Internet at http://www.regulations.govby searching for and locating Docket No. FAA-2015-
0498.

Examining the AD Docket

You may examine the AD docket on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2015-
0498; 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 Document 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: Bill Ashforth, Aerospace Engineer,
Airframe Branch, ANM-120S, FAA, Seattle Aircraft Certification Office
(ACO), 1601 Lind Avenue SW., Renton, WA 98057-3356; phone: 425-917-
6432; fax: 425-917-6590; email: bill.ashforth@faa.gov.

SUPPLEMENTARY INFORMATION:

Discussion

We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR
part 39 to supersede AD 2007-16-08, Amendment 39-15147 (72 FR 44728,
August 9, 2007). AD 2007-16-08 applied to all The Boeing Company Model
747-100, 747-100B, 747-100B SUD, 747-200B, 747-200C, 747-300, 747-400,
747-400D, and 747SR series airplanes. The NPRM published in the Federal
Register on March 30, 2015 (80 FR 16606). The NPRM was prompted by
reports of cracks found at the forward and aft inner chord strap and
angles on the station 800 frame on the left-side and right-side main
entry doors. The NPRM proposed to continue to require repetitive
inspections for cracking of the station 800 frame assembly, and repair
if necessary, and expand the inspection area. We are issuing this AD to
detect and correct fatigue cracks that could extend and fully sever the
frame, which could result in development of skin cracks that could lead
to rapid depressurization of the airplane.

Comments

We gave the public the opportunity to participate in developing
this AD. The following presents the comments received on the NPRM (80
FR 16606, March 30, 2015) and the FAA's response to each comment.

Support for the NPRM (80 FR 16606, March 30, 2015)

Boeing stated that it concurred with the contents of the NPRM (80
FR 16606, March 30, 2015).

Statement Regarding the NPRM (80 FR 16606, March 30, 2015)

United Airlines stated that it has reviewed the NPRM (80 FR 16606,
March 30, 2015), and has no comment to submit.

Request To Clarify Inspection Requirements

UPS requested that we add an additional statement to paragraph (i)
of the proposed AD (``Exception to the Service Information,'') to
clarify that the removal of fasteners is not required for performing
the surface high-frequency eddy current (HFEC) inspections specified by
paragraph (g) of the proposed AD (80 FR 16606, March 30, 2015). UPS
stated that by adding the clarification that the removal of fasteners
is not required, significant time and materials would be saved by
operators when accomplishing this inspection and prevent unnecessary
alternative method of compliance (AMOC) requests. UPS explained that
Boeing agreed in a response to a service request that fastener removal
is not required for performing surface HFEC inspections.
We agree because the clarification will reduce costs while ensuring
the same level of safety. We have added the following sentence to
paragraph (g) of this AD: ``It is not necessary to remove fasteners
while performing the surface HFEC inspections.''

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 change described previously and minor editorial
changes. We have determined that these minor changes:
Are consistent with the intent that was proposed in the
NPRM (80 FR

[[Page 65617]]

16606, March 30, 2015) for correcting the unsafe condition; and
Do not add any additional burden upon the public than was
already proposed in the NPRM (80 FR 16606, March 30, 2015).
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 Alert Service Bulletin 747-53A2451, Revision 2,
dated June 13, 2014. The service information describes procedures for
accomplishing repetitive inspections for cracking of the station 800
frame assembly, and repair. This service information is reasonably
available because the interested parties have access to it through
their normal course of business or by the means identified in the
ADDRESSES section of this AD.

Costs of Compliance

We estimate that this AD affects 124 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
----------------------------------------------------------------------------------------------------------------
Repetitive inspections........ Up to 53 work-hours x $85 $0 Up to $4,505 per Up to $558,620
per hour = $4,505 per inspection per inspection
inspection cycle. cycle. cycle.
----------------------------------------------------------------------------------------------------------------

We have received no definitive data that would enable us to provide
cost estimates for the on-condition actions specified in this AD.

Authority for This Rulemaking

Title 49 of the United States Code specifies the FAA's authority to
issue rules on aviation safety. Subtitle I, Section 106, describes the
authority of the FAA Administrator. Subtitle VII, Aviation Programs,
describes in more detail the scope of the Agency's authority.
We are issuing this rulemaking under the authority described in
Subtitle VII, Part A, Subpart III, Section 44701, ``General
requirements.'' Under that section, Congress charges the FAA with
promoting safe flight of civil aircraft in air commerce by prescribing
regulations for practices, methods, and procedures the Administrator
finds necessary for safety in air commerce. This regulation is within
the scope of that authority because it addresses an unsafe condition
that is likely to exist or develop on products identified in this
rulemaking action.

Regulatory Findings

We have determined that 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 removing Airworthiness Directive (AD)
2007-16-08, Amendment 39-15147 (72 FR 44728, August 9, 2007), and
adding the following new AD:

2015-22-01 The Boeing Company: Amendment 39-18305; Docket No. FAA-
2015-0498; Directorate Identifier 2014-NM-152-AD.

(a) Effective Date

This AD is effective December 1, 2015.

(b) Affected ADs

This AD replaces AD 2007-16-08, Amendment 39-15147 (72 FR 44728,
August 9, 2007).

This AD applies to all The Boeing Company Model 747-100, 747-
100B, 747-100B SUD, 747-200B, 747-200C, 747-300, 747-400, 747-400D,
and 747SR series airplanes, certificated in any category.

(d) Subject

Air Transport Association (ATA) of America Code 53, Fuselage.

(e) Unsafe Condition

This AD was prompted by reports of cracks found on the station
800 frame on the left-side and right-side main entry doors (MED), at
the forward and aft inner chord strap and angles, which are outside
the inspection area of AD 2007-16-08, Amendment 39-15147 (72 FR
44728, August 9, 2007). We are issuing this AD to detect and correct
fatigue cracks that could extend and fully sever the frame, which
could result in development of skin cracks that could lead to rapid
depressurization of the airplane.

(f) Compliance

Comply with this AD within the compliance times specified,
unless already done.

(g) Inspections of Station 800 Frame Assembly Between Stringer 14 and
Stringer 30

Except as required by paragraph (i) of this AD, at the
applicable time specified in paragraph 1.E., ``Compliance,'' of
Boeing Alert Service Bulletin 747-53A2451, Revision 2, dated June
13, 2014: Do a detailed inspection for cracking in the inner chord
strap, angles, and exposed web adjacent to the inner chords, and do
surface and open hole high-frequency eddy current (HFEC) inspections
for cracking in the inner chord strap and angles of the station 800
frame assembly between stringer 14 and stringer 30, in accordance
with the Accomplishment Instructions of Boeing Alert Service
Bulletin 747-53A2451, Revision 2, dated June 13, 2014. It is not
necessary to remove fasteners while performing the surface HFEC
inspections. Repeat the inspections at the applicable times
specified in paragraph 1.E., ``Compliance,'' of Boeing Alert Service
Bulletin 747-53A2451, Revision 2, dated June 13, 2014.

(h) Repair of Cracking

If any cracking is found during any inspection required by
paragraph (g) of this AD, before further flight, repair the cracking
using a method approved in accordance with

[[Page 65618]]

the procedures specified in paragraph (k) of this AD.

(i) Exception to the Service Information

(1) Where Boeing Alert Service Bulletin 747-53A2451, Revision 2,
dated June 13, 2014, specifies a compliance time ``after the
Revision 2 date of this service bulletin,'' this AD requires
compliance within the specified time after the effective date of
this AD.
(2) The Condition column of paragraph 1.E., ``Compliance,'' of
the Boeing Alert Service Bulletin 747-53A2451, Revision 2, dated
June 13, 2014, refers to total flight cycles ``as of the Revision 2
date of this service bulletin.'' This AD, however applies to
airplanes with the specified total flight cycles or total flight
hours as of the effective date of this AD.

(j) Credit for Previous Actions

This paragraph provides credit for the inspections and repairs
of the inner chord strap and angles of the station 800 frame
assembly between stringer 14 and stringer 18 required by paragraphs
(g) and (h) of this AD, if those actions were performed before the
effective date of this AD using Boeing Alert Service Bulletin 747-
53A2451, Revision 1, dated November 10, 2005, which was incorporated
by reference in AD 2006-12-12, Amendment 39-14638 (71 FR 33595, June
12, 2006).

(k) 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 (l)(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 required by this AD if it is approved by the
Boeing Commercial Airplanes Organization Designation Authorization
(ODA) that has been authorized by the Manager, Seattle ACO, to make
those findings. For a repair method to be approved, the repair must
meet the certification basis of the airplane, and the approval must
specifically refer to this AD.
(4) AMOCs approved for AD 2007-16-08, Amendment 39-15147 (72 FR
44728, August 9, 2007), are approved as AMOCs for the corresponding
provisions of this AD.

(l) Related Information

(1) For more information about this AD, contact Bill Ashforth,
Aerospace Engineer, Airframe Branch, ANM-120S, FAA, Seattle Aircraft
Certification Office (ACO), 1601 Lind Avenue SW., Renton, WA 98057-
3356; phone: 425-917-6432; fax: 425-917-6590; email:
bill.ashforth@faa.gov.
(2) Service information identified in this AD that is not
incorporated by reference is available at the addresses specified in
paragraphs (m)(3) and (m)(4) of this AD.

(m) Material Incorporated by Reference

(1) The Director of the Federal Register approved the
incorporation by reference (IBR) of the service information listed
in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51.
(2) You must use this service information as applicable to do
the actions required by this AD, unless the AD specifies otherwise.
(i) Boeing Alert Service Bulletin 747-53A2451, Revision 2, dated
June 13, 2014.
(ii) Reserved.
(3) For service information identified in this AD, contact
Boeing Commercial Airplanes, Attention: Data & Services Management,
P.O. Box 3707, MC 2H-65, Seattle, WA 98124-2207; telephone 206-544-
5000, extension 1; fax 206-766-5680; Internet https://www.myboeingfleet.com.
(4) You may view this service information at 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: http://www.archives.gov/federal-register/cfr/ibr-locations.html.

Issued in Renton, Washington, on October 19, 2015.
Jeffrey E. Duven,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2015-26979 Filed 10-26-15; 8:45 am]
BILLING CODE 4910-13-P

Federal Register / Vol. 80, No. 207 / Tuesday, October 27, 2015 / Rules and Regulations 65617

16606, March 30, 2015) for correcting Related Service Information Under 1 because the interested parties have
the unsafe condition; and CFR Part 51 access to it through their normal course
• Do not add any additional burden We reviewed Boeing Alert Service of business or by the means identified
upon the public than was already Bulletin 747–53A2451, Revision 2, in the ADDRESSES section of this AD.
proposed in the NPRM (80 FR 16606, dated June 13, 2014. The service Costs of Compliance
March 30, 2015). information describes procedures for
We also determined that these accomplishing repetitive inspections for We estimate that this AD affects 124
changes will not increase the economic cracking of the station 800 frame airplanes of U.S. registry.
burden on any operator or increase the assembly, and repair. This service We estimate the following costs to
scope of this AD. information is reasonably available comply with this AD:

ESTIMATED COSTS
Cost on U.S.
Action Labor cost Parts cost Cost per product operators

Repetitive inspections Up to 53 work-hours × $85 per hour = $4,505 per in- $0 Up to $4,505 per in- Up to $558,620 per
spection cycle. spection cycle. inspection cycle.

We have received no definitive data (4) Will not have a significant (d) Subject
that would enable us to provide cost economic impact, positive or negative, Air Transport Association (ATA) of
estimates for the on-condition actions on a substantial number of small entities America Code 53, Fuselage.
specified in this AD. under the criteria of the Regulatory (e) Unsafe Condition
Flexibility Act.
Authority for This Rulemaking This AD was prompted by reports of cracks
List of Subjects in 14 CFR Part 39 found on the station 800 frame on the left-
Title 49 of the United States Code
side and right-side main entry doors (MED),
specifies the FAA’s authority to issue Air transportation, Aircraft, Aviation at the forward and aft inner chord strap and
rules on aviation safety. Subtitle I, safety, Incorporation by reference, angles, which are outside the inspection area
Section 106, describes the authority of Safety. of AD 2007–16–08, Amendment 39–15147
the FAA Administrator. Subtitle VII, (72 FR 44728, August 9, 2007). We are
Aviation Programs, describes in more Adoption of the Amendment issuing this AD to detect and correct fatigue
detail the scope of the Agency’s cracks that could extend and fully sever the
authority. Accordingly, under the authority frame, which could result in development of
We are issuing this rulemaking under delegated to me by the Administrator, skin cracks that could lead to rapid
the authority described in Subtitle VII, the FAA amends 14 CFR part 39 as depressurization of the airplane.
Part A, Subpart III, Section 44701, follows: (f) Compliance
‘‘General requirements.’’ Under that Comply with this AD within the
PART 39—AIRWORTHINESS
section, Congress charges the FAA with compliance times specified, unless already
DIRECTIVES
promoting safe flight of civil aircraft in done.
air commerce by prescribing regulations (g) Inspections of Station 800 Frame
for practices, methods, and procedures ■ 1. The authority citation for part 39
continues to read as follows: Assembly Between Stringer 14 and Stringer
the Administrator finds necessary for 30
safety in air commerce. This regulation Authority: 49 U.S.C. 106(g), 40113, 44701.
Except as required by paragraph (i) of this
is within the scope of that authority AD, at the applicable time specified in
§ 39.13 [Amended]
because it addresses an unsafe condition paragraph 1.E., ‘‘Compliance,’’ of Boeing
that is likely to exist or develop on ■ 2. The FAA amends § 39.13 by Alert Service Bulletin 747–53A2451,
products identified in this rulemaking removing Airworthiness Directive (AD) Revision 2, dated June 13, 2014: Do a
action. 2007–16–08, Amendment 39–15147 (72 detailed inspection for cracking in the inner
chord strap, angles, and exposed web
Regulatory Findings FR 44728, August 9, 2007), and adding
adjacent to the inner chords, and do surface
the following new AD: and open hole high-frequency eddy current
We have determined that this AD will
not have federalism implications under 2015–22–01 The Boeing Company: (HFEC) inspections for cracking in the inner
Amendment 39–18305; Docket No. chord strap and angles of the station 800
Executive Order 13132. This AD will
FAA–2015–0498; Directorate Identifier frame assembly between stringer 14 and
not have a substantial direct effect on stringer 30, in accordance with the
2014–NM–152–AD.
the States, on the relationship between Accomplishment Instructions of Boeing Alert
the national government and the States, (a) Effective Date Service Bulletin 747–53A2451, Revision 2,
or on the distribution of power and This AD is effective December 1, 2015. dated June 13, 2014. It is not necessary to
responsibilities among the various remove fasteners while performing the
(b) Affected ADs surface HFEC inspections. Repeat the
levels of government.
For the reasons discussed above, I This AD replaces AD 2007–16–08, inspections at the applicable times specified
certify that this AD: Amendment 39–15147 (72 FR 44728, August in paragraph 1.E., ‘‘Compliance,’’ of Boeing
(1) Is not a ‘‘significant regulatory 9, 2007). Alert Service Bulletin 747–53A2451,
tkelley on DSK3SPTVN1PROD with RULES

Revision 2, dated June 13, 2014.
action’’ under Executive Order 12866, (c) Applicability
(2) Is not a ‘‘significant rule’’ under This AD applies to all The Boeing (h) Repair of Cracking
DOT Regulatory Policies and Procedures Company Model 747–100, 747–100B, 747– If any cracking is found during any
(44 FR 11034, February 26, 1979), 100B SUD, 747–200B, 747–200C, 747–300, inspection required by paragraph (g) of this
(3) Will not affect intrastate aviation 747–400, 747–400D, and 747SR series AD, before further flight, repair the cracking
in Alaska, and airplanes, certificated in any category. using a method approved in accordance with

VerDate Sep<11>2014 16:49 Oct 26, 2015 Jkt 238001 PO 00000 Frm 00011 Fmt 4700 Sfmt 4700 E:\FR\FM\27OCR1.SGM 27OCR1

65618 Federal Register / Vol. 80, No. 207 / Tuesday, October 27, 2015 / Rules and Regulations

the procedures specified in paragraph (k) of (2) Service information identified in this required inspections of each inboard
this AD. AD that is not incorporated by reference is and outboard tail rotor pitch link
available at the addresses specified in assembly for axial or radial bearing play,
(i) Exception to the Service Information paragraphs (m)(3) and (m)(4) of this AD.
(1) Where Boeing Alert Service Bulletin and if there was axial or radial bearing
747–53A2451, Revision 2, dated June 13, (m) Material Incorporated by Reference play, removing the tail rotor pitch link
2014, specifies a compliance time ‘‘after the (1) The Director of the Federal Register and inspecting for wear. Emergency AD
Revision 2 date of this service bulletin,’’ this approved the incorporation by reference 2015–16–51 was prompted by several
AD requires compliance within the specified (IBR) of the service information listed in this reports of worn tail rotor pitch link
time after the effective date of this AD. paragraph under 5 U.S.C. 552(a) and 1 CFR spherical bearings. We are issuing this
(2) The Condition column of paragraph part 51. supersedure to retain the inspection
1.E., ‘‘Compliance,’’ of the Boeing Alert (2) You must use this service information requirements in Emergency AD 2015–
Service Bulletin 747–53A2451, Revision 2, as applicable to do the actions required by
dated June 13, 2014, refers to total flight 16–51 while revising the applicability
this AD, unless the AD specifies otherwise.
cycles ‘‘as of the Revision 2 date of this (i) Boeing Alert Service Bulletin 747– and compliance time to clarify that all
service bulletin.’’ This AD, however applies 53A2451, Revision 2, dated June 13, 2014. Bell Model 429 helicopters require
to airplanes with the specified total flight (ii) Reserved. recurring inspections regardless of
cycles or total flight hours as of the effective (3) For service information identified in hours time-in-service (TIS) accumulated
date of this AD. this AD, contact Boeing Commercial on the helicopter. These actions are
(j) Credit for Previous Actions Airplanes, Attention: Data & Services intended to prevent pitch link failure
Management, P.O. Box 3707, MC 2H–65, and subsequent loss of control of the
This paragraph provides credit for the Seattle, WA 98124–2207; telephone 206–
inspections and repairs of the inner chord helicopter.
544–5000, extension 1; fax 206–766–5680;
strap and angles of the station 800 frame Internet https://www.myboeingfleet.com. DATES: This AD becomes effective
assembly between stringer 14 and stringer 18 (4) You may view this service information November 12, 2015.
required by paragraphs (g) and (h) of this AD, at FAA, Transport Airplane Directorate, 1601 We must receive comments on this
if those actions were performed before the Lind Avenue SW., Renton, WA. For
effective date of this AD using Boeing Alert
AD by December 28, 2015.
information on the availability of this
Service Bulletin 747–53A2451, Revision 1, ADDRESSES: You may send comments by
material at the FAA, call 425–227–1221.
dated November 10, 2005, which was (5) You may view this service information any of the following methods:
incorporated by reference in AD 2006–12–12, that is incorporated by reference at the • Federal eRulemaking Docket: Go to
Amendment 39–14638 (71 FR 33595, June National Archives and Records http://www.regulations.gov. Follow the
12, 2006). Administration (NARA). For information on online instructions for sending your
(k) Alternative Methods of Compliance the availability of this material at NARA, call comments electronically.
(AMOCs) 202–741–6030, or go to: http:// • Fax: 202–493–2251.
(1) The Manager, Seattle Aircraft www.archives.gov/federal-register/cfr/ibr- • Mail: Send comments to the U.S.
Certification Office (ACO), FAA, has the locations.html. Department of Transportation, Docket
authority to approve AMOCs for this AD, if Issued in Renton, Washington, on October Operations, M–30, West Building
requested using the procedures found in 14 19, 2015. Ground Floor, Room W12–140, 1200
CFR 39.19. In accordance with 14 CFR 39.19, Jeffrey E. Duven, New Jersey Avenue SE., Washington,
send your request to your principal inspector DC 20590–0001.
Manager, Transport Airplane Directorate,
or local Flight Standards District Office, as • Hand Delivery: Deliver to the
Aircraft Certification Service.
appropriate. If sending information directly
[FR Doc. 2015–26979 Filed 10–26–15; 8:45 am] ‘‘Mail’’ address between 9 a.m. and 5
to the manager of the ACO, send it to the
attention of the person identified in BILLING CODE 4910–13–P
p.m., Monday through Friday, except
paragraph (l)(1) of this AD. Information may Federal holidays.
be emailed to: 9-ANM-Seattle-ACO-AMOC- Examining the AD Docket
Requests@faa.gov. DEPARTMENT OF TRANSPORTATION
(2) Before using any approved AMOC, You may examine the AD docket on
notify your appropriate principal inspector, Federal Aviation Administration the Internet at http://
or lacking a principal inspector, the manager www.regulations.gov by searching for
of the local flight standards district office/ and locating Docket No. FAA–2015–
14 CFR Part 39
certificate holding district office.
4345; or in person at the Docket
(3) An AMOC that provides an acceptable [Docket No. FAA–2015–4345; Directorate
level of safety may be used for any repair Operations Office between 9 a.m. and 5
Identifier 2015–SW–049–AD; Amendment
required by this AD if it is approved by the 39–18306; AD 2015–22–02] p.m., Monday through Friday, except
Boeing Commercial Airplanes Organization Federal holidays. The AD docket
Designation Authorization (ODA) that has RIN 2120–AA64 contains this AD, the Transport Canada
been authorized by the Manager, Seattle Emergency AD, the economic
ACO, to make those findings. For a repair Airworthiness Directives; Bell evaluation, any comments received, and
method to be approved, the repair must meet Helicopter Textron Canada Limited other information. The street address for
the certification basis of the airplane, and the Helicopters the Docket Operations Office (telephone
approval must specifically refer to this AD.
(4) AMOCs approved for AD 2007–16–08, AGENCY: Federal Aviation 800–647–5527) is in the ADDRESSES
Amendment 39–15147 (72 FR 44728, August Administration (FAA), Department of section. Comments will be available in
9, 2007), are approved as AMOCs for the Transportation (DOT). the AD docket shortly after receipt. For
corresponding provisions of this AD. ACTION: Final rule; request for service information identified in this
(l) Related Information comments. AD, contact Bell Helicopter Textron
Canada Limited, 12,800 Rue de l’Avenir,
tkelley on DSK3SPTVN1PROD with RULES

(1) For more information about this AD, SUMMARY: We are superseding Mirabel, Quebec J7J1R4; telephone (450)
contact Bill Ashforth, Aerospace Engineer,
Airframe Branch, ANM–120S, FAA, Seattle
emergency airworthiness directive (AD) 437–2862 or (800) 363–8023; fax (450)
Aircraft Certification Office (ACO), 1601 Lind No. 2015–16–51 (Emergency AD 2015– 433–0272; or at http://
Avenue SW., Renton, WA 98057–3356; 16–51) for Bell Helicopter Textron www.bellcustomer.com/files/. You may
phone: 425–917–6432; fax: 425–917–6590; Canada Limited (Bell) Model 429 review the referenced service
email: bill.ashforth@faa.gov. helicopters. Emergency AD 2015–16–51 information at the FAA, Office of the

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Document Modified: 2015-12-14 15:35:49

Category		Regulatory Information
Collection		Federal Register
sudoc Class		AE 2.7: GS 4.107: AE 2.106:
Publisher		Office of the Federal Register, National Archives and Records Administration
Section		Rules and Regulations
Action		Final rule.
Dates		This AD is effective December 1, 2015.
Contact		Bill Ashforth, Aerospace Engineer, Airframe Branch, ANM-120S, FAA, Seattle Aircraft Certification Office (ACO), 1601 Lind Avenue SW., Renton, WA 98057-3356; phone: 425-917- 6432; fax: 425-917-6590; email: [email protected]
FR Citation		80 FR 65616
RIN Number		2120-AA64
CFR Associated		Air Transportation; Aircraft; Aviation Safety; Incorporation by Reference and Safety

80 FR 65616 - Airworthiness Directives; The Boeing Company Airplanes

DEPARTMENT OF TRANSPORTATIONFederal Aviation Administration

Federal Register Volume 80, Issue 207 (October 27, 2015)

DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration