Airworthiness Directives; The Boeing Company Airplanes, 41895-41897 [2012-16933]

Download as PDF Federal Register / Vol. 77, No. 137 / Tuesday, July 17, 2012 / Rules and Regulations Issued in Renton, Washington, on June 28, 2012. Kalene C. Yanamura, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2012–16637 Filed 7–16–12; 8:45 am] BILLING CODE 4910–13–P 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 Federal Aviation Administration (FAA), DOT. ACTION: Final rule. AGENCY: 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). sroberts on DSK5SPTVN1PROD with RULES SUMMARY: VerDate Mar<15>2010 19:47 Jul 16, 2012 Jkt 226001 41895 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 me.boecom@boeing.com; 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. powered by Pratt & Whitney JT9D series engines. Examining the AD Docket Request To Provide Credit for Previous Actions ADDRESSES: You may examine the AD docket on the Internet at https:// 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: rebel.nichols@faa.gov. SUPPLEMENTARY INFORMATION: 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 Frm 00011 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). 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 Discussion PO 00000 Comments Fmt 4700 Sfmt 4700 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 E:\FR\FM\17JYR1.SGM 17JYR1 41896 Federal Register / Vol. 77, No. 137 / Tuesday, July 17, 2012 / Rules and Regulations 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 U.S. registered airplanes Cost on U.S. operators Labor cost Replace deactivation pin, pin bushing, and pin insert (retained actions from existing AD 2002–19– 11, Amendment 39–12891 (67 FR 61478, October 1, 2002). Group 1: Install stowage bracket for deactivation pin (new action). Group 2: Replace bushing and deactivation pin and install stowage bracket for thrust reverser deactivation pin (new action). 12 work-hours × $85 per hour = $1,020 per inspection cycle. $12,108 $13,128 23 $301,944 17 work-hours × $85 per hour = $1,445. 17 work-hours × $85 per hour = $1,445. 14,644 16,089 16 257,424 19,972 21,417 7 149,919 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. sroberts on DSK5SPTVN1PROD with RULES Regulatory Findings VerDate Mar<15>2010 19:47 Jul 16, 2012 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. (a) Effective Date This airworthiness directive (AD) is effective August 21, 2012. List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. (d) Subject Joint Aircraft System Component (JASC)/ Air Transport Association (ATA) of America Code 7830, Thrust Reverser. 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 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. Jkt 226001 Parts cost Cost per product Action [Amended] 2. The FAA amends § 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. PO 00000 Frm 00012 Fmt 4700 Sfmt 4700 (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. (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 E:\FR\FM\17JYR1.SGM 17JYR1 Federal Register / Vol. 77, No. 137 / Tuesday, July 17, 2012 / Rules and Regulations sroberts on DSK5SPTVN1PROD with RULES 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) VerDate Mar<15>2010 19:47 Jul 16, 2012 Jkt 226001 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: 9-ANMSeattle-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) 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: rebel.nichols@faa.gov. 41897 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 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 DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2012–0703; Directorate Identifier 2010–SW–019–AD; Amendment 39–17112; AD 2012–13–10] RIN 2120–AA64 Airworthiness Directives; PZL Swidnik S.A. Helicopters Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule; request for comments. AGENCY: We are adopting a new airworthiness directive (AD) for the PZL Swidnik S.A. (PZL) Model PZL W–3A helicopter with a certain generator air outlet collector (collector) installed. This AD requires modifying the generator air outlet collector attachments (collector attachments). (l) Material Incorporated by Reference This AD is prompted by an incident (1) The Director of the Federal Register where cyclic control stick movement approved the incorporation by reference was restricted due to rotation of a loose (IBR) of the following service information under 5 U.S.C. 552(a) and 1 CFR part 51. collector, resulting in locking of the (2) You must use the following service longitudinal control system hydraulic information to do the actions required by this actuator fork end. These actions are AD, unless the AD specifies otherwise. intended to prevent rotation of the (i) Boeing Alert Service Bulletin 767– collector, which could lead to restricted 78A0089, Revision 5, dated June 9, 2009. cyclic control stick movement, and (3) The following service information was subsequent loss of control of the approved for IBR on November 5, 2002 (67 helicopter. FR 61478, October 1, 2002). (i) Boeing Alert Service Bulletin 767– DATES: This AD becomes effective 78A0089, Revision 1, dated May 30, 2002. August 1, 2012. (4) For service information identified in The Director of the Federal Register this AD, contact Boeing Commercial approved the incorporation by reference Airplanes, Attention: Data & Services of certain documents listed in this AD Management, P.O. Box 3707, MC 2H–65, as of August 1, 2012. Seattle, Washington 98124–2207; telephone We must receive comments on this 206–544–5000, extension 1; fax 206–766– 5680; email me.boecom@boeing.com; Internet AD by September 17, 2012. https://www.myboeingfleet.com. ADDRESSES: You may send comments by (5) You may review copies of the service any of the following methods: information at the FAA, Transport Airplane • Federal eRulemaking Docket: Go to Directorate, 1601 Lind Avenue SW., Renton, https://www.regulations.gov. Follow the Washington. For information on the online instructions for sending your availability of this material at the FAA, call comments electronically. 425–227–1221. • Fax: 202–493–2251. (6) You may also review copies of the • Mail: Send comments to the U.S. service information that is incorporated by reference at the National Archives and Department of Transportation, Docket PO 00000 Frm 00013 Fmt 4700 Sfmt 4700 SUMMARY: E:\FR\FM\17JYR1.SGM 17JYR1

Agencies

[Federal Register Volume 77, Number 137 (Tuesday, July 17, 2012)]
[Rules and Regulations]
[Pages 41895-41897]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2012-16933]


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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 me.boecom@boeing.com; 
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 https://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: rebel.nichols@faa.gov.

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: 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) 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: rebel.nichols@faa.gov.

(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 
me.boecom@boeing.com; 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: https://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
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