[Federal Register Volume 77, Number 159 (Thursday, August 16, 2012)]
[Proposed Rules]
[Pages 49396-49399]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2012-20108]


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

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2012-0809; Directorate Identifier 2011-NM-135-AD]
RIN 2120-AA64


Airworthiness Directives; The Boeing Company Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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

SUMMARY: We propose to supersede an existing airworthiness directive 
(AD) that applies to certain The Boeing Company Model 757 airplanes 
equipped with Rolls-Royce RB211-535E engines. The existing AD currently 
requires repetitive inspections for signs of damage of the aft hinge 
fittings and attachment bolts of the thrust reversers, and related 
investigative and corrective actions if necessary. The existing AD also 
provides for an optional terminating modification for the repetitive 
inspections. Since we issued the existing AD, we have received reports 
of incorrectly installed washers under the attachment bolts of the aft 
hinge fittings of the thrust reversers. For certain airplanes, this 
proposed AD would add a one-time inspection of the washers installed 
under the attachment bolts of the aft hinge fittings for correct 
installation sequence, and reinstallation if necessary. This proposed 
AD also adds an option for installing a redesigned aft hinge fitting 
with the trim already done, instead of trimming an existing or new 
hinge fitting, which is included in the existing optional terminating 
modification. We are proposing this AD to prevent failure of the 
attachment bolts and consequent separation of a thrust reverser from 
the airplane during flight, which could result in structural damage to 
the airplane.

DATES: We must receive comments on this proposed AD by October 1, 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 proposed 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; 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: Nancy Marsh, Aerospace Engineer, 
Airframe Branch, ANM-120S, FAA, Seattle Aircraft Certification Office, 
1601 Lind Avenue SW., Renton, Washington 98057-3356; phone: 425-917-
6440; fax: 425-917-6590; email: [email protected].

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-2012-0809; 
Directorate Identifier 2011-NM-135-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 June 8, 2008, we issued AD 2008-13-20, Amendment 39-15583 (73 FR 
37786, July 2, 2008), for certain Model 757 airplanes equipped with 
Rolls-Royce RB211-535E engines. That AD requires repetitive inspections 
for signs of damage of the aft hinge fittings and attachment bolts of 
the thrust reversers, and related investigative and corrective actions 
if necessary. That AD also provides for an optional terminating 
modification for the repetitive inspections. That AD resulted from 
reports of several incidents of bolt failure at the aft hinge fittings 
of the thrust reversers due to, among other things, high operational 
loads. We issued that AD to prevent failure of the attachment bolts and 
consequent separation of a thrust reverser from the airplane during 
flight, which could

[[Page 49397]]

result in structural damage to the airplane.

Actions Since Existing AD Was Issued

    Since we issued AD 2008-13-20, Amendment 39-15583 (73 FR 37786, 
July 2, 2008), we have received reports of incorrectly installed 
washers installed under the attachment bolts of the aft hinge fittings 
of the thrust reversers, due to an error in the original service 
information.

Relevant Service Information

    We reviewed Boeing Special Attention Service Bulletin 757-54-0049, 
Revision 1, dated September 23, 2009; and Revision 2, dated July 27, 
2011 (for Model 757-200, -200CB, and -200PF airplanes). We also 
reviewed Boeing Special Attention Service Bulletin 757-54-0050, 
Revision 1, dated October 7, 2009; and Revision 2, dated July 27, 2011 
(for Model 757-300 airplanes). For Group 1, Configuration 2 airplanes, 
Revision 1 of these service bulletins adds procedures for a detailed 
inspection of the washers installed under the attachment bolts of the 
aft hinge fittings for correct installation sequence, and if incorrect, 
removal and reinstallation of the washer stack up. Revision 2 of these 
service bulletins adds an option of installing a redesigned aft hinge 
fitting with the trim already done, instead of trimming an existing or 
new hinge fitting.

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 the same type design.

Proposed AD Requirements

    This proposed AD would retain all requirements of AD 2008-13-20, 
Amendment 39-15583 (73 FR 37786, July 2, 2008). For certain airplanes, 
this proposed AD would add a detailed inspection of the washers 
installed under the attachment bolts of the aft hinge fittings for 
correct installation sequence, and if incorrect, removal and 
reinstallation of the washer stack up. This proposed AD would also 
include an option (as part of the optional terminating action in the 
existing AD) for installing a redesigned aft hinge fitting designed 
with the trim already done, instead of trimming an existing or new 
hinge fitting, which is included in the existing optional terminating 
modification. This proposed AD would require accomplishing the actions 
specified in the service information described previously, except as 
discussed under ``Difference Between the Proposed AD and the Service 
Information.''

Difference Between the Proposed AD and the Service Information

    Although Boeing Special Attention Service Bulletins 757-54-0049 and 
757-54-0050, both Revision 2, both dated July 27, 2011, specify that 
you may contact the manufacturer for repair instructions, this proposed 
AD would require you to repair in one of the following ways:
     In accordance with a method that we approve; or
     Using data that meet the certification basis of the 
airplane, and that have been approved by the Boeing Commercial 
Airplanes Organization Designation Authorization (ODA) whom we have 
authorized to make those findings.

Costs of Compliance

    We estimate that this proposed AD affects 389 airplanes of U.S. 
registry.
    We estimate the following costs to comply with this proposed AD:

                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
                                                                                                Cost on U.S.
              Action                    Labor cost        Parts cost    Cost per product          operators
----------------------------------------------------------------------------------------------------------------
Retained inspections in AD 2008-   2 work-hours x $85             $0  $170 per inspection   $66,130 per
 13-20, Amendment 39-15583 (73 FR   per hour = $170 per                cycle.                inspection cycle.
 37786, July 2, 2008).              inspection cycle.
Optional modification in AD 2008-  61 work hours x $85         5,276  10,461..............  Up to $4,069,329.
 13-20 (includes new optional       per hour = $5,185.
 actions).
New proposed inspection..........  6 work-hours x $85              0  510.................  Up to $198,390.
                                    per hour = $510.
----------------------------------------------------------------------------------------------------------------

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

The Proposed Amendment

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

[[Page 49398]]

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) 2008-13-20, Amendment 39-15583 (73 FR 37786, July 2, 2008), and 
adding the following new AD:

The Boeing Company: Docket No. FAA-2012-0809; Directorate Identifier 
2011-NM-135-AD.

(a) Comments Due Date

    The FAA must receive comments on this AD action by October 1, 
2012.

(b) Affected ADs

    This AD supersedes AD 2008-13-20, Amendment 39-15583 (73 FR 
37786, July 2, 2008).

(c) Applicability

    This AD applies to The Boeing Company Model 757-200, -200CB, -
200PF, and -300 series airplanes, certificated in any category; 
equipped with Rolls-Royce RB211-535E engines.

(d) Subject

    Joint Aircraft System Component (JASC)/Air Transport Association 
(ATA) of America Code 54, Nacelles/Pylons.

(e) Unsafe Condition

    This AD results from reports of incorrectly installed washers 
under the attachment bolts of the aft hinge fittings of the thrust 
reversers. We are issuing this AD to prevent failure of the 
attachment bolts and consequent separation of a thrust reverser from 
the airplane during flight, which could result in structural damage 
to the airplane.

(f) Compliance

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

(g) Retained Repetitive Inspections/Investigative and Corrective 
Actions

    This paragraph restates the requirements of paragraph (f) of AD 
2008-13-20, Amendment 39-15583 (73 FR 37786, July 2, 2008), with 
revised service information. At the time specified in paragraph 1.E. 
``Compliance,'' of Boeing Special Attention Service Bulletin 757-54-
0049 or 757-54-0050, both dated July 16, 2007, as applicable; except 
as provided by paragraph (h) of this AD: Do a detailed inspection 
for signs of damage of the aft hinge fittings and attachment bolts 
of the thrust reversers by doing all the actions, including all 
applicable related investigative and corrective actions, as 
specified in the Accomplishment Instructions of the applicable 
service bulletins specified in paragraph (g)(1), (g)(2), or (g)(3); 
or paragraph (g)(4), (g)(5), or (g)(6) of this AD, as applicable. Do 
all applicable related investigative and corrective actions at the 
time specified in paragraph 1.E., ``Compliance'' of Boeing Special 
Attention Service Bulletin 757-54-0049 or 757-54-0050, both dated 
July 16, 2007. As of the effective date of this AD, only the service 
bulletin specified in paragraph (g)(3) or (g)(6) of this AD, as 
applicable, may be used to accomplish the actions required by this 
paragraph. If any damage is found and the service bulletin 
identified in paragraph (g)(1), (g)(2), (g)(3), (g)(4), (g)(5), or 
(g)(6) of this AD specifies to contact Boeing for appropriate 
action: Before further flight, repair using a method approved in 
accordance with the procedures specified in paragraph (n) of this 
AD.
    (1) Boeing Special Attention Service Bulletin 757-54-0049, dated 
July 16, 2007.
    (2) Boeing Special Attention Service Bulletin 757-54-0049, 
Revision 1, dated September 23, 2009.
    (3) Boeing Special Attention Service Bulletin 757-54-0049, 
Revision 2, dated July 27, 2011.
    (4) Boeing Service Bulletin 757-54-0050, dated July 16, 2007.
    (5) Boeing Special Attention Service Bulletin 757-54-0050, 
Revision 1, dated October 7, 2009.
    (6) Boeing Special Attention Service Bulletin 757-54-0050, 
Revision 2, dated July 27, 2011.

(h) Retained Exception to Service Information

    This paragraph restates the requirements of paragraph (g) of AD 
2008-13-20, Amendment 39-15583 (73 FR 37786, July 2, 2008). Where 
Boeing Special Attention Service Bulletin 757-54-0049 or Boeing 
Service Bulletin 757-54-0050, both dated July 16, 2007; as 
applicable; specifies compliance times relative to the date on the 
service bulletin, this AD requires compliance within the specified 
compliance time after August 6, 2008 (the effective date of AD 2008-
13-20).

(i) Retained Optional Terminating Modification

    This paragraph restates the actions specified in paragraph (h) 
of AD 2008-13-20, Amendment 39-15583 (73 FR 37786, July 2, 2008). 
Accomplishing the preventive modification identified in the service 
bulletins specified in paragraph (g)(1), (g)(2), or (g)(3); or 
paragraph (g)(4), (g)(5), or (g)(6) of this AD; as applicable; 
terminates the repetitive inspections required by paragraph (g) of 
this AD.

(j) Retained Concurrent Actions

    This paragraph restates the requirements of paragraph (i) of AD 
2008-13-20, Amendment 39-15583 (73 FR 37786, July 2, 2008). Prior to 
or concurrently with accomplishing the actions identified in the 
service bulletin specified in paragraph (g)(1), (g)(2), or (g)(3) of 
this AD; as applicable; accomplish the replacement specified in 
Boeing Special Attention Service Bulletin 757-54-0015, Revision 3, 
dated September 19, 1996.

(k) Retained Credit for Previous Actions

    This paragraph restates the provisions of paragraph (j) of AD 
2008-13-20, Amendment 39-15583 (73 FR 37786, July 2, 2008). This 
paragraph provides credit for the actions required by paragraph (j) 
of this AD, if those actions were performed before August 6, 2008 
(the effective date of AD 2008-13-20) using Boeing Service Bulletin 
757-54-0015, dated February 16, 1989; Revision 1, dated December 20, 
1990; or Revision 2, dated April 21, 1994 (which are not 
incorporated by reference in this AD).

(l) New Requirements of This AD: Inspection of Washer Stack Up 
Sequence/Corrective Action

    For Group 1, Configuration 2 airplanes: Within 3,000 flight 
cycles after the effective date of this AD, do a detailed inspection 
of the washers installed under the attachment bolts of the aft hinge 
fittings for correct installation sequence, in accordance with the 
Accomplishment Instructions of Boeing Special Attention Service 
Bulletin 757-54-0049 or 757-54-0050, both Revision 2, both dated 
July 27, 2011, as applicable. If an incorrect installation sequence 
is found, before further flight, remove and reinstall the washer 
stack up correctly, in accordance with the Accomplishment 
Instructions of Boeing Special Attention Service Bulletin 757-54-
0049 or 757-54-0050, both Revision 2, both dated July 27, 2011, as 
applicable.

(m) Credit for Previous Actions

    This paragraph provides credit for the actions required by 
paragraph (l) of this AD, if those actions were performed before the 
effective date of this AD using Boeing Special Attention Service 
Bulletin 757-54-0049, Revision 1, dated September 23, 2009; or 
Boeing Special Attention Service Bulletin 757-54-0050, Revision 1, 
dated October 7, 2009; as applicable.

(n) Alternative Methods of Compliance (AMOCs)

    (1) The Manager, Seattle Aircraft Certification Office (ACO), 
FAA, has the authority to approve AMOCs for this AD, if requested 
using the procedures found in 14 CFR 39.19. In accordance with 14 
CFR 39.19, send your request to your principal inspector or local 
Flight Standards District Office, as appropriate. If sending 
information directly to the manager of the ACO, send it to the 
attention of the person identified in 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) 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 previously in accordance with AD 2008-13-20, 
Amendment 39-15583 (73 FR 37786, July 2, 2008), are approved as 
AMOCs for the corresponding provisions of this AD.

[[Page 49399]]

(o) Related Information

    (1) For more information about this AD, contact Nancy Marsh, 
Aerospace Engineer, Airframe Branch, ANM-120S, FAA, Seattle Aircraft 
Certification Office, 1601 Lind Avenue SW., Renton, Washington 
98057-3356; phone: 425-917-6440; fax: 425-917-6590; email: 
[email protected].
    (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; 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 August 9, 2012.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2012-20108 Filed 8-15-12; 8:45 am]
BILLING CODE 4910-13-P