[Federal Register Volume 72, Number 153 (Thursday, August 9, 2007)]
[Rules and Regulations]
[Pages 44753-44756]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: E7-15419]


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

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2007-28920; Directorate Identifier 2007-NM-162-AD; 
Amendment 39-15152; AD 2007-16-13]
RIN 2120-AA64


Airworthiness Directives; Boeing Model 757-200, -200PF, and -
200CB Series Airplanes

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

ACTION: Final rule; request for comments.

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

SUMMARY: The FAA is superseding an existing airworthiness directive 
(AD) that applies to certain Boeing Model 757-200, -200PF, and -200CB 
series airplanes. The existing AD currently requires repetitive 
inspections of the shim installation between the vertical flange and 
bulkhead, and repair if necessary. This new AD adds, for certain 
airplanes, an inspection for cracking of the four critical fastener 
holes in the horizontal flange, and repair if necessary. This AD 
results from reports of cracking in the pylon under bolts that appear 
to be undamaged during the existing AD inspections. We are issuing this 
AD to detect and correct cracks, loose and broken bolts, and shim 
migration in the joint between the aft torque bulkhead and the strut-
to-diagonal brace fitting, which could result in damage to the strut 
and consequent separation of the strut and engine from the airplane.

DATES: This AD becomes effective August 24, 2007.
    The Director of the Federal Register approved the incorporation by 
reference of a certain publication listed in the AD as of August 24, 
2007.
    We must receive any comments on this AD by October 9, 2007.

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: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue, SE., Washington, DC 20590.
     Fax: (202) 493-2251.
     Hand Delivery: Room W12-140 on the ground floor of the 
West Building, 1200 New Jersey Avenue, SE., 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,

[[Page 44754]]

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 98057-3356; telephone (425) 
917-6450; fax (425) 917-6590.

SUPPLEMENTARY INFORMATION: 

Discussion

    On May 26, 2005, we issued AD 2005-12-04, amendment 39-14120 (70 FR 
34313, June 14, 2005). That AD applies to certain Boeing Model 757-200, 
-200PF, and -200CB series airplanes. That AD requires repetitive 
inspections of the shim installation between the vertical flange and 
bulkhead, and repair if necessary. That AD resulted from reports of 
cracks, loose and broken bolts, and shim migration in the joint between 
the aft torque bulkhead and the strut-to-diagonal brace fitting. The 
actions specified in that AD are intended to detect and correct such 
cracks, loose and broken bolts, and shim migration, which could result 
in damage to the strut and consequent separation of the strut and 
engine from the airplane.

Actions Since AD Was Issued

    Since we issued that AD, we have received reports of cracking in 
the pylon under bolts that appear to be undamaged during the existing 
AD inspections. Although the cracking was underneath non-discrepant 
bolts, it was adjacent to bolts subject to AD 2005-12-04 that were 
loose for a period of time long enough to cause this cracking.

Other Relevant Rulemaking

    On May 25, 2004, we issued AD 2004-12-07, amendment 39-13666 (69 FR 
33561, June 16, 2004), for certain Boeing Model 757 series airplanes. 
That AD requires, for certain airplanes, repetitive detailed 
inspections of certain aft bulkhead fasteners for loose or missing 
fasteners, and corrective action if necessary. That AD also requires, 
for certain other airplanes, a one-time detailed inspection of the 
middle gusset of the inboard side load fitting for proper alignment and 
realignment if necessary; a one-time eddy current inspection of certain 
fastener holes for cracking, and repair if necessary; and a detailed 
inspection of certain fasteners for loose or missing fasteners; and 
replacement with new fasteners if necessary. Accomplishing the actions 
specified in this AD terminates the requirements specified in 
paragraphs (b) and (c) of AD 2004-12-07.

Relevant Service Information

    We have reviewed Boeing Alert Service Bulletin 757-54A0047, 
Revision 3, dated June 27, 2007 (we referred to Boeing Service Bulletin 
757-54A0047, Revision 1, dated March 24, 2005, as the appropriate 
source of service information for accomplishing the required actions 
specified in AD 2005-12-04). The alert service bulletin describes 
basically the same procedures (as required by AD 2005-12-04) for 
repetitive detailed inspections of the shim installation between the 
vertical flange and bulkhead and repair if necessary; however, the 
description of the actions has been revised. The alert service bulletin 
specifies to do repetitive inspections as follows:
     Do detailed inspections of the shim installations between 
the vertical flange and bulkhead to determine if there are signs of 
movement.
     Do detailed inspections of the four fasteners in the 
vertical flange to determine if there are signs of movement or if there 
are gaps under the head or collar.
     Do detailed inspections of the fasteners that hold the 
strut to the horizontal flange of the strut-to-diagonal brace fitting 
to determine if there are signs of movement or if there are gaps under 
the head or collar.
    The alert service bulletin specifies to do related investigative 
actions and repairs as follows:
     Repair the shim if cumulative movement is 0.50 inch or 
less.
     Replace the shim if cumulative movement is more than 0.50 
inch and do the inspection and repair of the four critical fastener 
holes on the horizontal flange specified in Part IV of the alert 
service bulletin.
     If any fastener is rejected, inspect the fastener hole for 
cracking and repair if necessary, increase the diameter of the hole, 
install oversize fasteners, and do the inspection and repair of the 
four critical fastener holes on the horizontal flange specified in Part 
IV of the alert service bulletin.
    In addition to the repetitive inspections, the alert service 
bulletin describes procedures for an additional one-time inspection as 
follows: If any findings from inspections done in accordance with the 
original issue or Revision 1 of the service bulletin led to a rejection 
of any fasteners, or if there were any equivalent findings prior to the 
original issue of the service bulletin (except for findings on 
airplanes identified as Group 1, Configuration 2 in Revision 3 of the 
alert service bulletin that are prior to the incorporation of Boeing 
Service Bulletin 757-54-0035), the alert service bulletin describes a 
high frequency eddy current (HFEC) inspection for cracking of the four 
critical fastener holes in the horizontal flange and repair if 
necessary.
    Depending on the group and configuration specified in the alert 
service bulletin, the initial compliance time ranges from 90 days after 
the date on the service bulletin to 6,000 flight cycles or 36 months, 
whichever occurs first, after the incorporation of Boeing Service 
Bulletin 757-54-0035. Depending on the group and configuration 
specified in the alert service bulletin, the repetitive interval ranges 
from 6,000 flight cycles or 36 months, whichever occurs first, to 9,000 
flight cycles or 54 months, whichever occurs first.

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 supersede AD 2005-12-04. This new AD continues 
to require repetitive inspections of the shim installation between the 
vertical flange and bulkhead, and repair if necessary. This AD also 
requires, for certain airplanes, an inspection for cracking of the four 
critical fastener holes in the horizontal flange, and repair if 
necessary.

Differences Between This AD and the Alert Service Bulletin

    The alert service bulletin specifies to contact the manufacturer 
for instructions on how to repair certain conditions, but this AD 
requires repairing those conditions in one of the following ways:
     Using a method that we approve; or
     Using data that meet the certification basis of the 
airplane, and that have been approved by an Authorized Representative 
for the Boeing Commercial Airplanes Delegation Option Authorization 
Organization whom we have authorized to make those findings.

FAA's Determination of the Effective Date

    An unsafe condition exists that requires the immediate adoption of 
this AD; therefore, providing notice and opportunity for public comment 
before the AD is issued is impracticable, and 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

[[Page 44755]]

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-2007-28920; Directorate 
Identifier 2007-NM-162-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 Operations office between 9 
a.m. and 5 p.m., Monday through Friday, except Federal holidays. The 
Docket Operations office (telephone (800) 647-5527) is located on the 
ground level of the West 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 
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 part 39 of the Federal Aviation Regulations (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 
removing amendment 39-14120 (70 FR 34313, June 14, 2005) and adding the 
following new airworthiness directive (AD):

2007-16-13 Boeing: Docket No. FAA-2007-28920; Directorate Identifier 
2007-NM-162-AD; Amendment 39-15152.

Effective Date

    (a) This AD becomes effective August 24, 2007.

Affected ADs

    (b) This AD supersedes AD 2005-12-04. Accomplishing the actions 
specified in this AD terminates certain requirements of AD 2004-12-
07, amendment 39-13666.

Applicability

    (c) This AD applies to Boeing Model 757-200, -200PF, and -200CB 
series airplanes; certificated in any category; line numbers 1 
through 1048 inclusive; powered by Rolls-Royce engines.

Unsafe Condition

    (d) This AD results from reports of cracking in the pylon under 
bolts that appear to be undamaged during the existing AD 
inspections. We are issuing this AD to detect and correct cracks, 
loose and broken bolts, and shim migration in the joint between the 
aft torque bulkhead and the strut-to-diagonal brace fitting, which 
could result in damage to the strut and consequent separation of the 
strut and engine from 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.

Service Bulletin Reference

    (f) The term ``alert service bulletin,'' as used in this AD, 
means Boeing Alert Service Bulletin 757-54A0047, Revision 3, dated 
June 27, 2007.

One-Time Inspection and Repair

    (g) For airplanes identified in paragraphs (g)(1) and (g)(2) of 
this AD: Within 90 days after the effective date of this AD, do a 
high frequency eddy current (HFEC) inspection for cracking of the 
four critical fastener holes in the horizontal flange and, before 
further flight, do all applicable repairs, in accordance with Part 
IV of the Accomplishment Instructions of the alert service bulletin, 
except as required by paragraph (k) of this AD.
    (1) Airplanes on which findings on the horizontal or vertical 
fasteners or the shims led to a rejection of any fastener during the 
actions specified in Boeing Alert Service Bulletin 757-54A0047, 
dated November 13, 2003; or Boeing Service Bulletin 757-54A0047, 
Revision 1, dated March 24, 2005.
    (2) Airplanes that had equivalent findings prior to Boeing Alert 
Service Bulletin 757-54A0047, dated November 13, 2003, except for 
findings on airplanes identified as Group 1, Configuration 2 in the 
alert service bulletin that were prior to the incorporation of 
Boeing Service Bulletin 757-54-0035.

Repetitive Inspections and Repair

    (h) At the applicable times specified in paragraph 1.E., 
``Compliance,'' of the alert service bulletin, except as required by 
paragraphs (i) and (j) of this AD: Do the inspections specified in 
paragraphs (h)(1), (h)(2), and (h)(3) of this AD and, before further 
flight, do all applicable related investigative actions and repairs, 
by doing all the actions specified in Parts I and II of the 
Accomplishment Instructions of the alert service bulletin, except as 
required by paragraph (k) of this AD.
    (1) Do detailed inspections of the shim installations between 
the vertical flange and bulkhead to determine if there are signs of 
movement.
    (2) Do detailed inspections of the four fasteners in the 
vertical flange to determine

[[Page 44756]]

if there are signs of movement or if there are gaps under the head 
or collar.
    (3) Do detailed inspections of the fasteners that hold the strut 
to the horizontal flange of the strut-to-diagonal brace fitting to 
determine if there are signs of movement or if there are gaps under 
the head or collar.

Exceptions to Alert Service Bulletin Procedures

    (i) Where the alert service bulletin specifies a compliance time 
relative to ``the date on this service bulletin,'' this AD requires 
compliance within the corresponding specified time relative to the 
effective date of this AD.
    (j) Where the alert service bulletin specifies a compliance time 
relative to the ``date of issuance of airworthiness certificate,'' 
this AD requires compliance within the corresponding time relative 
to the date of issuance of the original standard airworthiness 
certificate or the date of issuance of the original export 
certificate of airworthiness.
    (k) If any crack is found during any inspection required by this 
AD, and the alert service bulletin specifies to contact Boeing for 
appropriate action: Before further flight, repair the crack using a 
method approved in accordance with the procedures specified in 
paragraph (o) of this AD

Credit for Actions Done Using Previous Service Information

    (l) Actions done before the effective date of this AD in 
accordance with Boeing Service Bulletin 757-54A0047, Revision 1, 
dated March 24, 2005; and Boeing Alert Service Bulletin 757-54A0047, 
Revision 2, dated January 31, 2007; are considered acceptable for 
compliance with the corresponding actions specified in this AD.
    (m) An inspection and corrective actions done before June 29, 
2005 (the effective date of AD 2005-12-04), in accordance with 
paragraph (b) or (c), as applicable, of AD 2004-12-07, are 
acceptable for compliance with the initial inspection requirement of 
paragraph (h) of this AD.

An Acceptable Method of Compliance With Certain Requirements of AD 
2004-12-07

    (n) Accomplishing the actions specified in this AD terminates 
the requirements specified in paragraphs (b) and (c) of AD 2004-12-
07.

Alternative Methods of Compliance (AMOCs)

    (o)(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) To request a different method of compliance or a different 
compliance time for this AD, follow the procedures in 14 CFR 39.19. 
Before using any approved AMOC on any airplane to which the AMOC 
applies, notify your appropriate principal inspector (PI) in the FAA 
Flight Standards District Office (FSDO), or lacking a PI, your local 
FSDO.
    (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.
    (4) AMOCs approved previously in accordance with AD 2004-12-07 
are approved as AMOCs for the corresponding provisions of this AD.
    (5) AMOCs approved previously in accordance with AD 2005-12-04 
are approved as AMOCs for the corresponding provisions of this AD.

Material Incorporated by Reference

    (p) You must use Boeing Alert Service Bulletin 757-54A0047, 
Revision 3, dated June 27, 2007, 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 FAA, Transport Airplane Directorate, 1601 
Lind Avenue, SW., Renton, Washington; or 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: 
http://www.archives.gov/federal-register/cfr/ibr-locations.html.

    Issued in Renton, Washington, on July 31, 2007.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
 [FR Doc. E7-15419 Filed 8-8-07; 8:45 am]
BILLING CODE 4910-13-P