[Federal Register Volume 70, Number 18 (Friday, January 28, 2005)]
[Proposed Rules]
[Pages 4050-4052]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 05-1586]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2005-20138; Directorate Identifier 2004-NM-167-AD]
RIN 2120-AA64


Airworthiness Directives; Boeing Model 757-200, -200PF, and -
200CB Series Airplanes Equipped With Pratt & Whitney or Rolls Royce 
Engines

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

ACTION: Notice of proposed rulemaking (NPRM).

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SUMMARY: The FAA proposes to adopt a new airworthiness directive (AD) 
for certain Boeing Model 757-200, -200PF, and -200CB series airplanes. 
This proposed AD would require inspecting to determine the part number 
of the upper link forward fuse pins of the engine struts; and replacing 
the fuse pins as necessary. This proposed AD is prompted by a report 
indicating that, due to an incorrect listing in the illustrated parts 
catalog, persons performing maintenance on the engine strut(s) could 
have installed an incorrect upper link forward fuse pin. We are 
proposing this AD to prevent a ruptured wing box, due to the engine not 
separating safely during certain emergency landing conditions, which 
could lead to a fuel spill and consequent fire.

DATES: We must receive comments on this proposed AD by March 14, 2005.

ADDRESSES: Use one of the following addresses to submit comments on 
this proposed 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.
     By fax: (202) 493-2251.
     Hand Delivery: Room PL-401 on the plaza level of the 
Nassif Building, 400 Seventh Street SW, Washington, DC, 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, P.O. Box 3707, Seattle, Washington 98124-
2207.
    You can examine the contents of this AD docket on the Internet at 
http://dms.dot.gov, or in person at the Docket Management Facility, 
U.S. Department of Transportation, 400 Seventh Street SW., room PL-401, 
on the plaza level of the Nassif Building, Washington, DC. This docket 
number is FAA-2005-20138; the directorate identifier for this docket is 
2004-NM-167-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:

Comments Invited

    We invite you to submit any relevant written data, views, or 
arguments regarding this proposed AD. Send your comments to an address 
listed under ADDRESSES. Include ``Docket No. FAA-2005-20138; 
Directorate Identifier 2004-NM-167-AD'' in the subject line of your 
comments. We specifically invite comments on the overall regulatory, 
economic, environmental, and energy aspects of the proposed AD. We will 
consider all comments submitted by the closing date and may amend the 
proposed AD in light of those comments.
    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 proposed AD. Using the search function of 
that website, 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 can review DOT's complete Privacy Act Statement in the 
Federal Register published on April 11, 2000 (65 FR 19477-78), or you 
can visit http://dms.dot.gov.

Examining the Docket

    You can 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 DMS receives them.

[[Page 4051]]

Discussion

    We have received a report indicating that, due to an incorrect 
listing in the illustrated parts catalog, an operator performing 
maintenance on the engine strut(s) could have installed, as a 
replacement for an upper link forward fuse pin having part number (P/N) 
311N5501-1, an incorrect fuse pin having P/N 311N5501-2. An incorrect 
fuse pin could prevent the engine from separating safely from the 
airplane upon abrupt contact with the ground or a massive ground object 
during an uncontrolled or wheels up emergency landing. This condition, 
if not corrected, could cause a ruptured wing box, due to the engine 
not separating safely during certain emergency landing conditions, 
which could lead to a fuel spill and consequent fire.

Relevant Service Information

    We have reviewed Boeing Special Attention Service Bulletin 757-54-
0048, dated May 13, 2004. The service bulletin describes procedures for 
inspecting to determine the part number of the upper link forward fuse 
pins of the engine struts and replacing the fuse pins with fuse pins 
having P/N 311N5501-1, if necessary. Accomplishing the actions 
specified in the service information is intended to adequately address 
the unsafe condition.

FAA's Determination and Requirements of the Proposed AD

    We have evaluated all pertinent information and identified an 
unsafe condition that is likely to exist or develop on other airplanes 
of this same type design. Therefore, we are proposing this AD, which 
would require accomplishing the actions specified in the service 
information described previously, except as discussed under 
``Differences Between the Proposed AD and Service Information.''

Differences Between the Proposed AD and Service Information

    Boeing Special Attention Service Bulletin 757-54-0048 specifies to 
inspect the upper link forward fuse pin to determine the P/N; however, 
we have examined a fuse pin returned from service and found the P/N to 
be unreadable. Therefore, we are proposing one alternate method of 
identifying the fuse pin by measuring the inside diameter of the fuse 
pin bore. We have coordinated the alternate method with the 
manufacturer and included appropriate procedures in this proposed AD.
    Boeing Special Attention Service Bulletin 757-54-0048 permits the 
use of an ``approved equivalent procedure'' for inspection and 
necessary replacement of the fuse pin(s); however, this proposed AD 
would require that inspection and replacement be done in accordance 
with the instructions of the aircraft maintenance manual (AMM) as 
specified in the service bulletin.

Clarification of Applicability

    Boeing Special Attention Service Bulletin 757-54-0048 specifies 
that it is applicable to airplanes having line numbers 1 through 735 
inclusive; however, airplanes having line numbers 1 through 618 
inclusive were originally manufactured with upper link forward fuse 
pins P/N 311N5060-1. P/N 311N5060-1 fuse pins are replaced with P/N 
311N5501-1 fuse pins when the strut improvement modification required 
by AD 2004-12-07, amendment 39-13666, (69 FR 33561, dated June 16, 
2004); or AD 2003-18-05, amendment 39-13296, (68 FR 53496, dated 
September 11, 2003); as applicable, is incorporated on the airplane.

Clarification of Inspection Terminology

    In this proposed AD, the ``detailed visual inspection'' specified 
in the Boeing service bulletin is referred to as a ``detailed 
inspection.'' We have included the definition for a detailed inspection 
in Note 1 of the proposed AD.

Costs of Compliance

    There are about 735 airplanes of the affected design in the 
worldwide fleet. This proposed AD would affect about 478 airplanes of 
U.S. registry. The proposed inspection would take about 1 work hour per 
fuse pin (2 fuse pins per airplane), at an average labor rate of $65 
per work hour. Based on these figures, the estimated cost of the 
proposed AD for U.S. operators is $62,140, or $130 per airplane.
    Replacement of any upper link forward fuse pin, if required, would 
take about 26 work hours, at an average labor rate of $65 per work 
hour. Required parts would cost about $431. Based on these figures, the 
estimated cost of a proposed replacement is $2,121 per fuse pin.

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); 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 proposed AD. 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, 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:

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 adding the following new 
airworthiness directive (AD):

Boeing: Docket No. FAA-2005-20138; Directorate Identifier 2004-NM-
167-AD.

[[Page 4052]]

Comments Due Date

    (a) The Federal Aviation Administration (FAA) must receive 
comments on this AD action by March 14, 2005.

Affected ADs

    (b) None.

Applicability

    (c) This AD applies to Boeing Model 757-200, -200PF, and -300 
series airplanes, line numbers 1 through 735 inclusive, certificated 
in any category; equipped with Pratt & Whitney or Rolls Royce 
engines.

Unsafe Condition

    (d) This AD was prompted by a report indicating that, due to an 
incorrect listing in the illustrated parts catalog, persons 
performing maintenance on the engine strut(s) could have installed 
an incorrect upper link forward fuse pin having part number (P/N) 
311N5501-2. We are issuing this AD to prevent a ruptured wing box, 
due to the engine not separating safely during certain emergency 
landing conditions, which could lead to a fuel spill and consequent 
fire.

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.

Inspection of Fuse Pin

    (f) Within 24 months after the effective date of this AD, 
perform a detailed inspection to determine the P/N of the upper link 
forward fuse pins of the engine struts, in accordance with the 
Accomplishment Instructions of Boeing Special Attention Service 
Bulletin 757-54-0048, dated May 13, 2004, except as provided in 
paragraph (g) of this AD.

    Note 1: For the purposes of this AD, a detailed inspection is: 
``An intensive examination of a specific item, installation, or 
assembly to detect damage, failure, or irregularity. Available 
lighting is normally supplemented with a direct source of good 
lighting at an intensity deemed appropriate. Inspection aids such as 
mirror, magnifying lenses, etc., may be necessary. Surface cleaning 
and elaborate procedures may be required.''

    (1) If the fuse pin is P/N 311N5501-1 or P/N 311N5060-1, no 
further action is required for that fuse pin.
    (2) If the fuse pin is P/N 311N5501-2, prior to further flight, 
replace the fuse pin with a new or serviceable fuse pin, P/N 
311N5501-1, in accordance with the Accomplishment Instructions of 
the service bulletin.
    (3) If the P/N of the fuse pin cannot be determined by 
inspection, use a tool such as an inside reading micrometer to 
determine the inside diameter (ID) of the fuse pin bore.
    (i) If the ID of the fuse pin bore is greater than or equal to 
0.850 inch, no further action is required for that fuse pin.
    (ii) If the ID of the fuse pin bore is less than 0.850 inch, 
prior to further flight, replace the fuse pin as specified in 
paragraph (f)(2) of this AD.
    (g) Where Boeing Special Attention Service Bulletin 757-54-0048 
permits the use of an ``approved equivalent procedure'' for access 
and replacement of the fuse pin(s), this AD requires that access and 
replacement be done in accordance with the instructions of the 
aircraft maintenance manual (AMM) as specified in the service 
bulletin.

Parts Installation

    (h) As of the effective date of this AD, no person may install a 
fuse pin, P/N 311N5501-2, on any airplane identified in the 
applicability of this AD.

Alternative Methods of Compliance (AMOCs)

    (i)(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) An AMOC that provides an acceptable level of safety may be 
used for any repair required by this AD, if it is approved by a 
Boeing Company Designated Engineering Representative who has been 
authorized by the Manager, Seattle ACO, to make those findings. For 
a repair method to be approved, the approval must specifically refer 
to this AD.

    Issued in Renton, Washington, on January 18, 2005.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 05-1586 Filed 1-27-05; 8:45 am]
BILLING CODE 4910-13-P