[Federal Register Volume 77, Number 137 (Tuesday, July 17, 2012)]
[Rules and Regulations]
[Pages 41895-41897]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2012-16933]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2012-0147; Directorate Identifier 2011-NM-067-AD;
Amendment 39-17116; AD 2012-14-02]
RIN 2120-AA64
Airworthiness Directives; The Boeing Company Airplanes
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Final rule.
-----------------------------------------------------------------------
SUMMARY: We are superseding an existing airworthiness directive (AD)
for certain The Boeing Company Model 767-200 and -300 series airplanes.
That AD currently requires replacement of the existing deactivation
pin, aft cascade pin bushing, and pin insert on each thrust reverser
half with new, improved components. This new AD requires a dye
penetrant inspection for cracking of the rivet holes of the bushing
plate and repair or replacement, if necessary; and for certain
airplanes, replacing the existing bushing with a new bushing and
deactivation pin, and installing a new or serviceable stowage bracket
for the deactivation pins on all airplanes powered by Pratt & Whitney
JT9D series engines. This AD was prompted by reports that certain
airplanes require installation of a new bushing and deactivation pin
with increased load carrying capability and all airplanes powered by
Pratt & Whitney JT9D series engines require installation of a new
bracket for stowing the deactivation pin. We are issuing this AD to
prevent failure of the thrust reverser deactivation pins, which could
fail to prevent a deployment of a deactivated thrust reverser in flight
and consequent reduced controllability of the airplane.
DATES: This AD is effective August 21, 2012.
The Director of the Federal Register approved the incorporation by
reference of a certain publication listed in the AD as of August 21,
2012.
The Director of the Federal Register approved the incorporation by
reference of a certain other publication listed in this AD as of
November 5, 2002 (67 FR 61478, October 1, 2002).
ADDRESSES: For service information identified in this AD, contact
Boeing Commercial Airplanes, Attention: Data & Services Management,
P.O. Box 3707, MC 2H-65, Seattle, Washington 98124-2207; telephone 206-
544-5000, extension 1; fax 206-766-5680; email [email protected];
Internet https://www.myboeingfleet.com. You may review copies of the
referenced service information at the FAA, Transport Airplane
Directorate, 1601 Lind Avenue SW., Renton, Washington. For information
on the availability of this material at the FAA, call 425-227-1221.
Examining the AD Docket
You may examine the AD docket on the Internet at http://www.regulations.gov; 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: Rebel Nichols, Aerospace Engineer,
Propulsion Branch, ANM-140S, FAA, Seattle Aircraft Certification Office
(ACO), 1601 Lind Avenue SW., Renton, Washington 98057-3356; phone: 425-
917-6509; fax: 425-917-6590; email: [email protected].
SUPPLEMENTARY INFORMATION:
Discussion
We issued a Notice of Proposed Rulemaking (NPRM) to amend 14 CFR
part 39 to supersede AD 2002-19-11, Amendment 39-12891 (67 FR 61478,
October 1, 2002). That AD applies to the specified products. The NPRM
published in the Federal Register on February 22, 2012 (77 FR 10406).
That NPRM proposed to continue to require replacement of the existing
deactivation pin, aft cascade pin bushing, and pin insert on each
thrust reverser half with new, improved components. That NPRM also
proposed to require a dye penetrant inspection for cracking of the
rivet holes of the bushing plate and repair or replacement, if
necessary; and for certain airplanes, replacing the existing bushing
with a new bushing and deactivation pin, and installing a new or
serviceable stowage bracket for the deactivation pins on all airplanes
powered by Pratt & Whitney JT9D series engines.
Comments
We gave the public the opportunity to participate in developing
this AD. The following presents the comments received on the proposal
(77 FR 10406, February 22, 2012) and the FAA's response to each
comment.
Support for Proposed Rule (77 FR 10406, February 22, 2012)
Boeing concurs with the content of the proposed rule (77 FR 10406,
February 22, 2012).
Request To Provide Credit for Previous Actions
Atlas Air requested that we revise the NPRM (77 FR 10406, February
22, 2012) to provide credit for actions required by paragraph (h)(2) of
the NPRM, if those actions were accomplished before the effective date
of the AD using Boeing Service Bulletin 767-78A0089, Revision 3, dated
December 18, 2003.
We agree. Paragraph (i) of the NPRM (77 FR 10406, February 22,
2012) provided credit for actions required by paragraph (g) of the NPRM
if those actions were performed before the effective date of the NPRM
using Boeing Service Bulletin 767-78A0089, Revision 2, dated March 13,
2003; Boeing Service Bulletin 767-78A0089, Revision 3, dated December
18, 2003; or Boeing Service Bulletin 767-78A0089, Revision 4, dated
March 6, 2008. We have revised paragraph (i) of this final rule to also
provide credit for actions required by paragraph (h)(2) of this AD, if
those actions were performed before the effective date of this AD.
Explanation of Changes Made to This AD
We have revised certain headings throughout this AD and revised
Note 1 of the NPRM (77 FR 10406, February 22, 2012) to paragraph (g)(2)
of this AD. We have also revised paragraph (i) of this AD. These
changes have not affected the intent of those paragraphs.
Explanation of Updated Credit Language
We have revised the heading and wording for paragraph (i) of this
AD to provide appropriate credit for previous accomplishment of certain
actions. This change does not affect the intent of that paragraph.
Conclusion
We reviewed the relevant data, considered the comments received,
and determined that air safety and the public interest require adopting
the AD
[[Page 41896]]
with the change described previously. We have determined that these
minor changes:
Are consistent with the intent that was proposed in the
NPRM (77 FR 10406, February 22, 2012) for correcting the unsafe
condition; and
Do not add any additional burden upon the public than was
already proposed in the NPRM (77 FR 10406, February 22, 2012).
We also determined that these changes will not increase the
economic burden on any operator or increase the scope of the AD.
Costs of Compliance
We estimate that this AD affects 23 airplanes of U.S. registry.
We estimate the following costs to comply with this AD:
Estimated Costs
----------------------------------------------------------------------------------------------------------------
Number of
Cost per U.S. Cost on U.S.
Action Labor cost Parts cost product registered operators
airplanes
----------------------------------------------------------------------------------------------------------------
Replace deactivation pin, pin 12 work-hours x $12,108 $13,128 23 $301,944
bushing, and pin insert $85 per hour =
(retained actions from $1,020 per
existing AD 2002-19-11, inspection
Amendment 39-12891 (67 FR cycle.
61478, October 1, 2002).
Group 1: Install stowage 17 work-hours x 14,644 16,089 16 257,424
bracket for deactivation pin $85 per hour =
(new action). $1,445.
Group 2: Replace bushing and 17 work-hours x 19,972 21,417 7 149,919
deactivation pin and install $85 per hour =
stowage bracket for thrust $1,445.
reverser deactivation pin
(new action).
----------------------------------------------------------------------------------------------------------------
We have received no definitive data that would enable us to provide
cost estimates for the on-condition actions (repair or replacement of
bushing plate) 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)
2002-19-11, Amendment 39-12891 (67 FR 61478, October 1, 2002), and
adding the following new AD:
2012-14-02 The Boeing Company: Amendment 39-17116; Docket No. FAA-
2012-0147; Directorate Identifier 2011-NM-067-AD.
(a) Effective Date
This airworthiness directive (AD) is effective August 21, 2012.
(b) Affected ADs
This AD supersedes AD 2002-19-11, Amendment 39-12891 (67 FR
61478, October 1, 2002).
(c) Applicability
This AD applies to The Boeing Company Model 767-200 and -300
series airplanes, certificated in any category; as identified in
Boeing Alert Service Bulletin 767-78A0089, Revision 5, dated June 9,
2009.
(d) Subject
Joint Aircraft System Component (JASC)/Air Transport Association
(ATA) of America Code 7830, Thrust Reverser.
(e) Unsafe Condition
This AD was prompted by reports that certain airplanes require
installation of a new bushing and deactivation pin with increased
load carrying capability and all airplanes powered by Pratt &
Whitney JT9D series engines require installation of a new bracket
for stowing the deactivation pin. We are issuing this AD to prevent
failure of the thrust reverser deactivation pins, which could fail
to prevent a deployment of a deactivated thrust reverser in flight
and consequent reduced controllability of the airplane.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(g) Retained Replacement of Deactivation Pin, Pin Bushing, and Pin
Insert
(1) This paragraph restates the requirements of paragraph (a) of
AD 2002-19-11, Amendment 39-12891 (67 FR 61478, October 1, 2002),
with revised service
[[Page 41897]]
information. Within 24 months after November 5, 2002 (the effective
date of AD 2002-19-11, Amendment 39-12891 (67 FR 61478, October 1,
2002)), replace the existing deactivation pin, pin bushing in the
aft cascade mounting ring, and pin insert on each thrust reverser
half, with new, improved components, in accordance with Boeing Alert
Service Bulletin 767-78A0089, Revision 1, dated May 30, 2002; or
Boeing Alert Service Bulletin 767-78A0089, Revision 5, dated June 9,
2009. After the effective date of this AD, only Boeing Alert Service
Bulletin 767-78A0089, Revision 5, dated June 9, 2009, may be used.
(2) The new, improved insert flange and pin bushing does not
physically preclude use of a deactivation pin having P/N 315T1604-2
or -5. However, use of deactivation pins having P/N 315T1604-2 or -5
may not prevent the thrust reversers from deploying in the event of
a full powered deployment. Therefore, thrust reversers modified per
AD 2002-19-11, Amendment 39-12891 (67 FR 61478, October 1, 2002),
are required to be installed with the new, longer deactivation pins
having P/N 315T1604-6, as specified in Boeing Alert Service Bulletin
767-78A0089, Revision 1, dated May 30, 2002; or Boeing Alert Service
Bulletin 767-78A0089, Revision 5, dated June 9, 2009. After the
effective date of this AD, only Boeing Alert Service Bulletin 767-
78A0089, Revision 5, dated June 9, 2009, may be used to install the
new, longer deactivation pins.
(h) New Inspection, Bushing and Pin Replacement, and Installation of
Stowage Bracket
Within 24 months after the effective date of this AD, do the
applicable actions specified in paragraphs (h)(1) and (h)(2) of this
AD.
(1) For Group 2 airplanes, as identified in Boeing Alert Service
Bulletin 767-78A0089, Revision 5, dated June 9, 2009, do a dye
penetrant inspection for cracking of the rivet holes and replace any
P/N 315T3222-3 or P/N 315T3222-10 bushing and deactivation pin with
a new or serviceable P/N 315T3221-1 bushing and new P/N 315T1604-6
deactivation pin, in accordance with the Accomplishment Instructions
of Boeing Alert Service Bulletin 767-78A0089, Revision 5, dated June
9, 2009. If any crack is found in the rivet holes of the bushing
plate, before further flight, repair or replace the bushing plate
with a new or serviceable bushing plate, as applicable, using a
method approved in accordance with the procedures specified in
paragraph (j) of this AD.
(2) For both Group 1 and Group 2 airplanes, as identified in
Boeing Alert Service Bulletin 767-78A0089, Revision 5, dated June 9,
2009, install a new or serviceable stowage bracket assembly (P/N
015T0196-4 for the right thrust reverser, P/N 015T0196-5 for the
left thrust reverser), in accordance with the Accomplishment
Instructions of Boeing Alert Service Bulletin 767-78A0089, Revision
5, dated June 9, 2009.
(i) Credit for Previous Actions
This paragraph provides credit for the actions specified in
paragraphs (g) and (h)(2) of this AD, if those actions were
performed before the effective date of this AD using Boeing Service
Bulletin 767-78A0089, Revision 2, dated March 13, 2003; Boeing
Service Bulletin 767-78A0089, Revision 3, dated December 18, 2003;
or Boeing Service Bulletin 767-78A0089, Revision 4, dated March 6,
2008.
(j) 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 the Related Information
section of this AD. Information may be emailed to: [email protected].
(2) Before using any approved AMOC, notify your appropriate
principal inspector, or lacking a principal inspector, the manager
of the local flight standards district office/certificate holding
district office.
(3) AMOCs approved previously in accordance with AD 2002-19-11,
Amendment 39-12891 (67 FR 61478, October 1, 2002), are approved as
AMOCs for the corresponding provisions of paragraph (g) of this AD.
(k) Related Information
For more information about this AD, contact Rebel Nichols,
Aerospace Engineer, Propulsion Branch, ANM-140S, FAA, Seattle
Aircraft Certification Office (ACO), 1601 Lind Avenue SW., Renton,
Washington 98057-3356; phone: 425-917-6509; fax: 425-917-6590;
email: [email protected].
(l) Material Incorporated by Reference
(1) The Director of the Federal Register approved the
incorporation by reference (IBR) of the following service
information under 5 U.S.C. 552(a) and 1 CFR part 51.
(2) You must use the following service information to do the
actions required by this AD, unless the AD specifies otherwise.
(i) Boeing Alert Service Bulletin 767-78A0089, Revision 5, dated
June 9, 2009.
(3) The following service information was approved for IBR on
November 5, 2002 (67 FR 61478, October 1, 2002).
(i) Boeing Alert Service Bulletin 767-78A0089, Revision 1, dated
May 30, 2002.
(4) For service information identified in this AD, contact
Boeing Commercial Airplanes, Attention: Data & Services Management,
P.O. Box 3707, MC 2H-65, Seattle, Washington 98124-2207; telephone
206-544-5000, extension 1; fax 206-766-5680; email
[email protected]; Internet https://www.myboeingfleet.com.
(5) You may review copies of the service information at the FAA,
Transport Airplane Directorate, 1601 Lind Avenue SW., Renton,
Washington. For information on the availability of this material at
the FAA, call 425-227-1221.
(6) You may also review copies of the 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 June 29, 2012.
Kalene C. Yanamura,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2012-16933 Filed 7-16-12; 8:45 am]
BILLING CODE 4910-13-P