Document ID: FAA-2012-0147-0001
Agency: faa
Document Type: Proposed Rule
Title: Airworthiness Directives: Boeing Co. Airplanes
Posted Date: 2012-02-22T05:00Z

[Federal Register Volume 77, Number 35 (Wednesday, February 22, 2012)]
[Proposed Rules]
[Pages 10406-10408]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2012-4162]

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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]
RIN 2120-AA64

Airworthiness Directives; The Boeing Company Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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SUMMARY: We propose to supersede an existing airworthiness directive 
(AD) that applies to certain The Boeing Company Model 767-200 and -300 
series airplanes. The existing AD requires replacement of the existing 
deactivation pin, aft cascade pin bushing, and pin insert on each 
thrust reverser half with new, improved components. Since we issued 
that AD, we received 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. This proposed AD would add a dye penetrant inspection 
for cracking of the rivet holes of the bushing plate and repair or 
replacement, if necessary. For certain airplanes, this proposed AD 
would require 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. We are proposing 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: We must receive comments on this proposed AD by April 9, 2012.

ADDRESSES: You may send comments, using the procedures found in 14 CFR 
11.43 and 11.45, by any of the following methods:
     Federal eRulemaking Portal: Go to http://www.regulations.gov. Follow the instructions for submitting comments.
     Fax: 202-493-2251.
     Mail: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue SE., Washington, DC 20590.
     Hand Delivery: Deliver to Mail address above between 9 
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
    For service information identified in this 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 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 proposed AD, the regulatory 
evaluation, any comments received, and other information. The street 
address for the Docket Office (phone: 800-647-5527) is in the ADDRESSES 
section. Comments will be available in the AD docket shortly after 
receipt.

FOR FURTHER INFORMATION CONTACT: 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:

Comments Invited

    We invite you to send any written relevant data, views, or 
arguments about this proposed AD. Send your comments to an address 
listed under the ADDRESSES section. Include ``Docket No. FAA-2012-0147; 
Directorate Identifier 2011-NM-067-AD'' at the beginning of your 
comments. We specifically invite comments on the overall regulatory, 
economic, environmental, and energy aspects of this proposed AD. We 
will consider all comments received by the closing date and may amend 
this proposed AD because of those comments.
    We will post all comments we receive, without change, to http://www.regulations.gov, including any personal information you provide. We 
will also post a report summarizing each substantive verbal contact we 
receive about this proposed AD.

Discussion

    On September 19, 2002, we issued AD 2002-19-11, Amendment 39-12891 
(67 FR 61478, October 1, 2002), for certain Model 767-200 and -300 
series airplanes powered by Pratt & Whitney JT9D series engines. The 
existing AD requires replacement of the existing deactivation pin, aft 
cascade pin bushing, and pin insert on each thrust reverser half, with 
new, improved components. The existing AD resulted from reports that 
the pin insert for the deactivation pin was not able to withstand the 
load of a powered deployment and could fail on some airplanes. We 
issued that AD to prevent failure of the thrust reverser deactivation 
pins, which could fail to

[[Page 10407]]

prevent a deployment of a deactivated thrust reverser in flight and 
consequent reduced controllability of the airplane.

Actions Since Existing AD Was Issued

    Since we issued AD 2002-19-11, Amendment 39-12891 (67 FR 61478, 
October 1, 2002), we received reports indicating that certain airplanes 
require installation of a new bushing and 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. Specifically, we have been advised that the part 
number (P/N) 315T3222-3 bushing could not be replaced by the P/N 
315T3222-10 bushing due to inadequate edge margin on the early thrust 
reverser configuration.

Relevant Service Information

    AD 2002-19-11, Amendment 39-12891 (67 FR 61478, October 1, 2002), 
refers to Boeing Alert Service Bulletin 767-78A0089, Revision 1, dated 
May 30, 2002, as the appropriate source of service information for the 
required actions. Boeing has since revised this service information. We 
reviewed Boeing Alert Service Bulletin 767-78A0089, Revision 5, dated 
June 9, 2009, which identifies additional work that needs to be 
performed on specifically configured Group 2 airplanes for doing a dye 
penetrant inspection for cracking of the rivet holes of the bushing 
plate; repair or replacement of the bushing plate with a new or 
serviceable bushing plate if necessary; and replacing any existing P/N 
315T3222-3 or P/N 315T3222-10 bushing and deactivation pin with a new 
P/N 315T3221-1 bushing and new P/N 315T1604-6 deactivation pin to 
provide adequate edge margin. Boeing Alert Service Bulletin 767-
78A0089, Revision 5, dated June 9, 2009, also identifies additional 
work for installing a new or serviceable stowage bracket for the 
deactivation pins on all airplanes powered by Pratt & Whitney JT9D 
series engines.

FAA's Determination

    We are proposing this AD because we evaluated all the relevant 
information and determined the unsafe condition described previously is 
likely to exist or develop in other products of these same type 
designs.

Proposed AD Requirements

    This proposed AD would retain all requirements of AD 2002-19-11, 
Amendment 39-12891 (67 FR 61478, October 1, 2002). This proposed AD 
would also require accomplishing the actions specified in the service 
information described previously.

Change to Existing AD

    Since AD 2002-19-11, Amendment 39-12891 (67 FR 61478, October 1, 
2002), was issued, the AD format has been revised, and certain 
paragraphs have been rearranged. As a result, paragraphs (a) and (b) of 
AD 2002-19-11 Amendment 39-12891 (67 FR 61478, October 1, 2002), have 
been re-identified as paragraphs (g) and (h) in this proposed AD.

Costs of Compliance

    We estimate that this proposed AD affects 23 airplanes of U.S. 
registry. We estimate the following costs to comply with this proposed 
AD:

                                                                     Estimated Costs
--------------------------------------------------------------------------------------------------------------------------------------------------------
                                                                                                                         Number of U.S.
                     Action                                   Labor cost                 Parts cost        Cost per        registered      Cost on U.S.
                                                                                                           product         airplanes        operators
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Replace deactivation pin, pin bushing, and pin    12 work-hours x $85 per hour =              $12,108          $13,128               23         $301,944
 insert (retained actions from existing AD 2002-   $1,020 per inspection cycle.
 19-11, Amendment 39[dash]12891 (67 FR 61478,
 October 1, 2002).
Group 1: Install stowage bracket for              17 work-hours x $85 per hour =               14,644           16,089               16          257,424
 deactivation pin (new proposed action).           $1,445.
Group 2: Replace bushing and deactivation pin     17 work-hours x $85 per hour =               19,972           21,417                7          149,919
 and install stowage bracket for thrust reverser   $1,445.
 deactivation pin (new proposed 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 proposed AD.

Authority for This Rulemaking

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

Regulatory Findings

    We have determined that this proposed AD would not have federalism 
implications under Executive Order 13132. This proposed AD would not 
have a substantial direct effect on the States, on the relationship 
between the national Government and the States, or on the distribution 
of power and responsibilities among the various levels of government.
    For the reasons discussed above, I certify that the proposed 
regulation:
    (1) Is not a ``significant regulatory action'' under Executive 
Order 12866,
    (2) Is not a ``significant rule'' under the DOT Regulatory Policies 
and Procedures (44 FR 11034, February 26, 1979),
    (3) Will not affect intrastate aviation in Alaska, and
    (4) Will not have a significant economic impact, positive or 
negative, on a substantial number of small entities under the criteria 
of the Regulatory Flexibility Act.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Incorporation by 
reference, Safety.

[[Page 10408]]

The Proposed Amendment

    Accordingly, under the authority delegated to me by the 
Administrator, the FAA proposes to amend 14 CFR part 39 as follows:

PART 39--AIRWORTHINESS DIRECTIVES

    1. The authority citation for part 39 continues to read as follows:

    Authority:  49 U.S.C. 106(g), 40113, 44701.

Sec.  39.13  [Amended]

    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:

The Boeing Company: Docket No. FAA-2012-0147; Directorate Identifier 
2011-NM-067-AD.

 (a) Comments Due Date

    The FAA must receive comments on this AD action by April 9, 
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.

Restatement of Requirements of AD 2002-19-11, Amendment 39-12891 (67 FR 
61478, October 1, 2002), With Revised Service Information

(g) Replacement of Deactivation Pin, Pin Bushing, and Pin Insert

    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.

    Note to paragraph (g): 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.

New Requirements of This AD

(h) 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 Actions Accomplished in Accordance With Previous Service 
Information

    Actions accomplished before the effective date of this AD in 
accordance with Boeing Alert Service Bulletin 767-78A0089, Revision 
2, dated March 13, 2003; Boeing Alert Service Bulletin 767-78A0089, 
Revision 3, dated December 18, 2003; or Boeing Alert Service 
Bulletin 767-78A0089, Revision 4, dated March 6, 2008; are 
considered acceptable for compliance with the corresponding 
requirements of paragraph (g) of this AD.

(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 for 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

    (1) 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.
    (2) 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.

    Issued in Renton, Washington, on February 10, 2012.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2012-4162 Filed 2-21-12; 8:45 am]
BILLING CODE 4910-13-P