[Federal Register Volume 71, Number 80 (Wednesday, April 26, 2006)]
[Rules and Regulations]
[Pages 24571-24573]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 06-3891]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2006-24557; Directorate Identifier 2006-NM-082-AD; 
Amendment 39-14572; AD 2006-09-02]
RIN 2120-AA64


Airworthiness Directives; Boeing Model 757-200 and -200PF Series 
Airplanes Equipped With Pratt & Whitney Engines

AGENCY: Federal Aviation Administration (FAA), Department of 
Transportation (DOT).

ACTION: Final rule; request for comments.

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SUMMARY: The FAA is adopting a new airworthiness directive (AD) for 
certain Boeing Model 757-200 and -200PF series airplanes equipped with 
Pratt & Whitney engines. This AD requires repetitive detailed 
inspections to detect and correct any gap between the strut fitting and 
the forward engine mount assembly and applicable related investigative 
actions, corrective actions, and other specified actions. This AD 
results from a report indicating that gaps had been found between the 
strut fitting and the forward engine mount assembly. We are issuing 
this AD to detect and correct any gaps between the strut fitting and 
the forward engine mount assembly of both engines, which could result 
in separation of the engine from the wing and subsequent loss of 
control of the airplane.

DATES: This AD becomes effective May 11, 2006.
    The Director of the Federal Register approved the incorporation by 
reference of a certain publication listed in the AD as of May 11, 2006.
    We must receive comments on this AD by June 26, 2006.

ADDRESSES: Use one of the following addresses to submit comments on 
this AD.
     DOT Docket Web site: Go to http://dms.dot.gov and follow 
the instructions for sending your comments electronically.
     Government-wide rulemaking Web site: Go to http://www.regulations.gov and follow the instructions for sending your 
comments electronically.
     Mail: Docket Management Facility; U.S. Department of 
Transportation, 400 Seventh Street, SW., Nassif Building, Room PL-401, 
Washington, DC 20590.
     Fax: (202) 493-2251.
     Hand Delivery: Room PL-401 on the plaza level of the 
Nassif Building,

[[Page 24572]]

400 Seventh Street, SW., Washington, DC, between 9 a.m. and 5 p.m., 
Monday through Friday, except Federal holidays.
    Contact Boeing Commercial Airplanes, P.O. Box 3707, Seattle, 
Washington 98124-2207, for service information identified in this AD.

FOR FURTHER INFORMATION CONTACT: Dennis Stremick, Aerospace Engineer, 
Airframe Branch, ANM-120S, FAA, Seattle Aircraft Certification Office, 
1601 Lind Avenue, SW., Renton, Washington 98055-4056; telephone (425) 
917-6450; fax (425) 917-6590.

SUPPLEMENTARY INFORMATION:

Discussion

    We have received a report indicating that gaps have been found 
between the strut fitting and the forward engine mount assembly above 
the Number 1 engine on Boeing Model 757-200 and -200PF series 
airplanes. The gap was caused by the loosening of vertical tension 
bolts that were installed on the forward engine mount installation. The 
gap at the two forward engine mount bolts was \3/16\ of an inch and the 
gap at the aft two engine mount bolts was \1/8\ of an inch. In 
addition, wear damage was also found on the surfaces of the forward 
engine mount assembly and the strut fitting. This condition, if not 
corrected, could result in separation of the engine from the wing and 
subsequent loss of control of the airplane.

Relevant Service Information

    We have reviewed Boeing Alert Service Bulletin (ASB) 757-71A0085, 
dated March 2, 2006.
    Part 1 of the Accomplishment Instructions of the ASB describes 
procedures for an initial detailed inspection to detect gaps between 
the strut fitting and the forward engine mount assembly of both 
engines. Part 1 also describes the following related investigative 
actions, corrective actions, and other specified actions. If there is 
no gap found, Part 1 specifies applying inspection torque to each 
engine mount bolt and applying torque stripe between each bolt and 
forward engine mount surface. Part 1 also specifies, for certain 
limits, applying installation torque to all the bolts. If there is a 
gap between the strut fitting and forward engine mount assembly at a 
bolt location, Part 1 specifies a detailed inspection to detect damage 
of the parts and repairing or replacing parts. In addition, Part 1 
advises operators to write to Boeing if necessary for repair 
information.
    Part 2 of the Accomplishment Instructions of the ASB describes 
similar procedures for repetitive detailed inspections to detect gaps 
between the strut fitting and the forward engine mount assembly of both 
engines. Part 2 also describes the following related investigative 
actions, corrective actions, and other special actions. If there is no 
gap found but the torque stripe on one or more bolts is cracked, broken 
or missing, Part 2 specifies applying an inspection torque to each 
forward engine mount bolt and applying a new torque stripe between each 
bolt and forward engine mount surface. Part 2 also specifies, if there 
is a gap found between the strut fitting and forward engine mount 
assembly at a bolt location, performing a detailed inspection for 
damage of the forward engine mount and strut fitting and repairing or 
replacing any damaged parts. In addition, Part 2 advises operators to 
write to Boeing if necessary for repair information.

FAA's Determination and Requirements of This AD

    The unsafe condition described previously is likely to exist or 
develop on other airplanes of the same type design. For this reason, we 
are issuing this AD to detect and correct any gaps between the strut 
fitting and the forward engine mount assembly. This AD requires 
accomplishing the actions specified in the service information 
described previously, except as discussed under ``Differences Between 
the AD and the ASB.''

Differences Between the AD and the ASB

    Although the ASB specifies repairing or replacing, if damage is 
found on parts before subsequent flights, it also advises operators to 
write to the manufacturer if necessary for repair information. We have 
clarified in Note 1 of this AD that any deviation from the 
Accomplishment Instructions provided in the ASB must be approved as an 
alternative method of compliance under paragraph (h) of this AD.

Interim Action

    This is considered to be interim action. The manufacturer has 
advised that it currently is developing a modification that will 
address the unsafe condition identified in this AD. Once this 
modification is developed, approved, and available, the FAA may 
consider additional rulemaking.

FAA's Determination of the Effective Date

    Since an unsafe condition exists that requires the immediate 
adoption of this AD, we have found that notice and opportunity for 
public comment before issuing this AD are impracticable, and that good 
cause exists to make this AD effective in less than 30 days.

Comments Invited

    This AD is a final rule that involves requirements that affect 
flight safety and was not preceded by notice and an opportunity for 
public comment; however, we invite you to submit any relevant written 
data, views, or arguments regarding this AD. Send your comments to an 
address listed in the ADDRESSES section. Include ``Docket No. FAA-2006-
24557; Directorate Identifier 2006-NM-082-AD'' at the beginning of your 
comments. We specifically invite comments on the overall regulatory, 
economic, environmental, and energy aspects of the AD that might 
suggest a need to modify it.
    We will post all comments we receive, without change, to http://dms.dot.gov, including any personal information you provide. We will 
also post a report summarizing each substantive verbal contact with FAA 
personnel concerning this AD. Using the search function of that Web 
site, anyone can find and read the comments in any of our dockets, 
including the name of the individual who sent the comment (or signed 
the comment on behalf of an association, business, labor union, etc.). 
You may review the DOT's complete Privacy Act Statement in the Federal 
Register published on April 11, 2000 (65 FR 19477-78), or you may visit 
http://dms.dot.gov.

Examining the Docket

    You may examine the AD docket on the Internet at http://dms.dot.gov, or in person at the Docket Management Facility office 
between 9 a.m. and 5 p.m., Monday through Friday, except Federal 
holidays. The Docket Management Facility office (telephone (800) 647-
5227) is located on the plaza level of the Nassif Building at the DOT 
street address stated in the ADDRESSES section. Comments will be 
available in the AD docket shortly after the Docket Management System 
receives them.

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

[[Page 24573]]

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 the 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); and
    3. 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.
    We prepared a regulatory evaluation of the estimated costs to 
comply with this AD and placed it in the AD docket. See the ADDRESSES 
section for a location to examine the regulatory evaluation.

List of Subjects in 14 CFR Part 39

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

Adoption of the Amendment

0
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 Federal Aviation Administration (FAA) amends Sec.  39.13 by 
adding the following new airworthiness directive (AD):

2006-09-02 Boeing: Amendment 39-14572. Docket No. FAA-2006-24557; 
Directorate Identifier 2006-NM-082-AD.

Effective Date

    (a) This AD becomes effective May 11, 2006.

Affected ADs

    (b) None.

Applicability

    (c) This AD applies to Boeing Model 757-200 and -200PF series 
airplanes, certificated in any category, equipped with Pratt & 
Whitney engines, as identified in Boeing Alert Service Bulletin 
(ASB) 757-71A0085, dated March 2, 2006.

Unsafe Condition

    (d) This AD results from a report indicating that gaps had been 
found between the strut fitting and the forward engine mount 
assembly. We are issuing this AD to detect and correct any gaps 
found between the strut fitting and the forward engine mount 
assembly of both engines, which could result in separation of the 
engine from the wing and subsequent loss of control of the airplane.

Compliance

    (e) You are responsible for having the actions required by this 
AD performed within the compliance times specified, unless the 
actions have already been done.

Initial Inspection

    (f) Within 90 days after the effective date of this AD or within 
3,000 flight cycles since the most recent installation of each 
engine, whichever occurs later: For each engine, perform a detailed 
inspection to detect any gap between the strut fitting and the 
forward engine mount assembly of the engine, and before further 
flight, do all applicable related investigative actions, corrective 
actions, and other specified actions; in accordance with Part 1 of 
the Accomplishment Instructions of Boeing ASB 757-71A0085, dated 
March 2, 2006.

    Note 1:  In the Accomplishment Instructions of the ASB, the 
manufacturer provides instructions to repair or replace parts before 
``subsequent'' flight if damage is found on parts. However, the 
manufacturer also specifies to write to the manufacturer if 
necessary for repair information. This AD requires that any 
deviation from the instructions provided in the ASB must be approved 
as an alternative method of compliance under paragraph (h) of this 
AD.

Repetitive Inspections

    (g) Within 3,000 flight cycles after accomplishing the 
requirements of paragraph (f) of this AD: Perform a detailed 
inspection to detect any gap between the strut fitting and the 
forward mount assembly of both engines, and before further flight, 
do all applicable related investigative actions, corrective actions, 
and other specified actions; in accordance with Part 2 of the 
Accomplishment Instructions of Boeing ASB 757-71A0085, dated March 
2, 2006. Thereafter, repeat the actions specified in Part 2 of the 
Accomplishment Instructions of the ASB at intervals not to exceed 
3,000 flight cycles.

Alternative Methods of Compliance (AMOCs)

    (h)(1) The Manager, Seattle Aircraft Certification Office (ACO), 
FAA, has the authority to approve AMOCs for this AD, if requested in 
accordance with the procedures found in 14 CFR 39.19.
    (2) Before using any AMOC approved in accordance with Sec.  
39.19 on any airplane to which the AMOC applies, notify the 
appropriate principal inspector in the FAA Flight Standards 
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 an 
Authorized Representative for the Boeing Commercial Airplanes 
Delegation Option Authorization Organization who 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.

Material Incorporated by Reference

    (i) You must use Boeing Alert Service Bulletin 757-71A0085, 
dated March 2, 2006, to perform the actions that are required by 
this AD, unless the AD specifies otherwise. The Director of the 
Federal Register approved the incorporation by reference of this 
document in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. 
Contact Boeing Commercial Airplanes, P.O. Box 3707, Seattle, 
Washington 98124-2207, for a copy of this service information. You 
may review copies at the Docket Management Facility, U.S. Department 
of Transportation, 400 Seventh Street, SW., Room PL-401, Nassif 
Building, Washington, DC; on the Internet at http://dms.dot.gov; or 
at the National Archives and Records Administration (NARA). For 
information on the availability of this material at the NARA, call 
(202) 741-6030, or go to http://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html.

    Issued in Renton, Washington, on April 17, 2006.
Kalene C. Yanamura,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 06-3891 Filed 4-25-06; 8:45 am]
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