[Federal Register Volume 71, Number 80 (Wednesday, April 26, 2006)]
[Rules and Regulations]
[Pages 24573-24576]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 06-3890]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2005-23313; Directorate Identifier 2005-NM-111-AD; 
Amendment 39-14573; AD 2006-09-03]
RIN 2120-AA64


Airworthiness Directives; Boeing Model 727, 727C, 727-100, and 
727-100C Series Airplanes

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

ACTION: Final rule.

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SUMMARY: The FAA is adopting a new airworthiness directive (AD) for all

[[Page 24574]]

Boeing Model 727, 727C, 727-100, and 727-100C series airplanes. This AD 
requires repetitive inspections for cracks in the body skin and bear 
strap at the upper and lower hinge cutouts of the mid-cabin galley 
doorway, along the upper fastener row of the stringer 14R lap splice, 
and in the doorstop fitting adjacent to the upper hinge cutout; and 
corrective action if necessary. This AD also provides for optional 
terminating action for certain inspections. This AD results from 
reports of skin and bear strap cracking at the upper and lower hinge 
cutout and along the upper fastener row of the stringer 14R lap splice, 
and cracking in the doorstop fitting adjacent to the upper hinge 
cutout. There are also reports of cracking on airplanes previously 
modified in production to resist such cracking. We are issuing this AD 
to find and fix fatigue cracking of the fuselage, which could result in 
reduced structural integrity and consequent rapid decompression of the 
airplane.

DATES: This AD becomes effective May 31, 2006.
    The Director of the Federal Register approved the incorporation by 
reference of a certain publication listed in the AD as of May 31, 2006.

ADDRESSES: You may examine the 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., Nassif Building, 
Room PL-401, Washington, DC.
    Contact Boeing Commercial Airplanes, P.O. Box 3707, Seattle, 
Washington 98124-2207, for the service information identified in this 
AD.

FOR FURTHER INFORMATION CONTACT: Daniel F. Kutz, Aerospace Engineer, 
Airframe Branch, ANM-120S, FAA, Seattle Aircraft Certification Office, 
1601 Lind Avenue, SW., Renton, Washington 98055-4056; telephone (425) 
917-6456; fax (425) 917-6590.

SUPPLEMENTARY INFORMATION:

Examining the Docket

    You may examine the airworthiness directive (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 street address stated in the ADDRESSES section.

Discussion

    The FAA issued a notice of proposed rulemaking (NPRM) to amend 14 
CFR part 39 to include an AD that would apply to all Boeing Model 727, 
727C, 727-100, and 727-100C series airplanes. That NPRM was published 
in the Federal Register on December 15, 2005 (70 FR 74237). That NPRM 
proposed to require repetitive inspections for cracks in the body skin 
and bear strap at the upper and lower hinge cutouts of the mid-cabin 
galley doorway, along the upper fastener row of the stringer 14R lap 
splice, and in the doorstop fitting adjacent to the upper hinge cutout; 
and corrective action if necessary. That NPRM also proposed to provide 
for optional terminating action for certain inspections.

Comments

    We provided the public the opportunity to participate in the 
development of this AD. We have considered the comments received from 
one commenter, the airplane manufacturer.

Request To Clarify Description of the Unsafe Condition

    Boeing asks that the description of the unsafe conditions, as 
specified in paragraph (d) of the NPRM, be changed for clarification, 
to add the following: ``There are also reports of cracking on airplanes 
modified in production to resist such cracking.'' Boeing states that 
``The modification installed in production was to enlarge the cutout 
radius. This did not prevent cracking, but rather resisted and delayed 
cracking to a later time.''
    We infer that Boeing is asking for a change to the Summary section, 
as well as the second sentence in paragraph (d) of this AD. These 
paragraphs describe what prompted the AD. In the Discussion section of 
the NPRM we did note that modifications done in production did not 
prevent cracking. Therefore, we agree to clarify paragraph (d) and the 
Summary section as follows: ``There are also reports of cracking on 
airplanes previously modified in production to resist such cracking.''

Request To Change the Discussion Section

    Boeing asks that the eighth and ninth sentences in the Discussion 
section of the NPRM be changed. Those sentences are as follows: ``Some 
of the cracks were found on airplanes that were modified in service by 
increasing the radius of the corners of the body skin at the hinge 
cutouts, and installing doublers at the high cutouts; and airplanes on 
which the equivalent modification was done in production. These 
modifications did not prevent the cracking.'' Boeing asks that those 
sentences be changed to the following: ``Some of the cracks found on 
airplanes that were modified in production by increasing the radius of 
the cutout corners of the body skin hinge cutouts (sic). This 
modification did not prevent the cracking.'' Boeing states that this 
would correctly reflect that production modifications included only 
increasing the skin cutout radius and did not include installing skin 
doublers in the hinge areas. Boeing adds that production records 
indicate that no doublers were installed in production.
    We acknowledge Boeing's concern and agree with the comment. No 
cracks have been reported yet on airplanes that were modified in 
service using Boeing Service Bulletin 727-53-0054, which increases the 
radius of the cutout corners of the body skin hinge cutouts, and adds 
skin doublers in the hinge areas. However, the ``Discussion'' section 
is included in an NPRM as background information on the unsafe 
condition to provide adequate information to the public during the 
comment period. The ``Discussion'' section is not included in the final 
rule. We have made no change to the AD in this regard.

Request To Change the Other Relevant Rulemaking Section

    Boeing asks that the fifth sentence in the Other Relevant 
Rulemaking section of the NPRM be changed. That sentence specifies 
``One of the structural modifications in that AD is of the body skin of 
the mid-galley door hinge cutouts done in accordance with Boeing 
Service Bulletin 727-53-0054, Revision 1, dated November 16, 1989.'' 
Boeing asks that the sentence be changed to the following, ``One of the 
structural modifications in that AD is of the body skin of the mid-
galley door hinge cutouts, done in accordance with Boeing Service 
Bulletin 727-53-0054, initial release, dated June 26, 1968, with 
additional instructions shown in Boeing Document D6-54860, Rev C, page 
3.2.1 for Boeing Service Bulletin 727-53-0054.'' Boeing states that the 
airplane effectivity specified in Revision 1 increased by three 
airplanes.
    We acknowledge Boeing's concern and agree with the comment. In 
addition, we note that Boeing Document D6-54860, Rev C, specifies the 
airplane effectivity per the latest revision of the service bulletin, 
which is Service Bulletin 727-53-0054, Revision 1, which did include 
three additional airplanes. However, the ``Other Relevant Rulemaking'' 
section of the NPRM is not included in the final rule. We have made no 
change to the AD in this regard.

[[Page 24575]]

Conclusion

    We have carefully reviewed the available data, including the 
comments received, and determined that air safety and the public 
interest require adopting the AD with the changes described previously. 
We have determined that these changes will neither increase the 
economic burden on any operator nor increase the scope of the AD.

Costs of Compliance

    There are about 232 airplanes of the affected design in the 
worldwide fleet. This AD affects about 123 airplanes of U.S. registry. 
The following table provides the estimated costs for U.S. operators to 
comply with this AD, per inspection cycle.

                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
                                                                               Average hourly       Cost per
                      Airplane group                           Work hours        labor rate         airplane
----------------------------------------------------------------------------------------------------------------
Group 1, Configuration 1..................................                10               $65              $650
Group 1, Configuration 2..................................                10                65               650
Group 1, Configuration 3..................................                 9                65               585
Group 2...................................................                 9                65               585
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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 this AD:
    (1) Is not a ``significant regulatory action'' under Executive 
Order 12866;
    (2) Is not a ``significant rule'' under 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):

2006-09-03 Boeing: Amendment 39-14573. Docket No. FAA-2005-23313; 
Directorate Identifier 2005-NM-111-AD.

Effective Date

    (a) This AD becomes effective May 31, 2006.

Affected ADs

    (b) This AD is related to AD 98-11-03, amendment 39-10530, as 
corrected by AD 98-11-03 R1, amendment 39-10983.

Applicability

    (c) This AD applies to all Boeing Model 727, 727C, 727-100 and 
727-100C series airplanes, certificated in any category.

Unsafe Condition

    (d) This AD results from reports of skin and bear strap cracking 
at the upper and lower hinge cutout and along the upper fastener row 
of the stringer 14R lap splice, and cracking in the doorstop fitting 
adjacent to the upper hinge cutout. There are also reports of 
cracking on airplanes previously modified in production to resist 
such cracking. We are issuing this AD to find and fix fatigue 
cracking of the fuselage, which could result in reduced structural 
integrity and consequent rapid decompression 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.

Service Bulletin Reference

    (f) The term ``alert service bulletin,'' as used in this AD, 
means Boeing Alert Service Bulletin 727-53A0228, dated March 24, 
2005.

Repetitive Inspections

    (g) Accomplish the applicable inspections for any cracks 
(including stop-drilled, trimmed-out, or repaired cracks) in the 
body skin and bear strap at the upper and lower hinge cutouts of the 
mid-cabin galley doorway, along the upper fastener row of the 
stringer 14R lap splice, and in the doorstop fitting adjacent to the 
upper hinge cutout, as specified in Table 1 of paragraph 1.E. 
``Compliance'' of the alert service bulletin. Accomplish the 
inspections at the applicable compliance time specified in Table 1 
of paragraph 1.E.; except, where Table 1 specifies a compliance time 
relative to the date of the release of the alert service bulletin, 
this AD requires compliance relative to the effective date of this 
AD. Accomplish the inspections by doing all the applicable actions 
specified in the Accomplishment Instructions of the alert service 
bulletin. Inspections of door stop fittings made of 7075 material 
having part number (P/N) 65-23674-7 are not required. Repeat the 
applicable inspection at the applicable repeat interval specified in 
Table 1 of paragraph 1.E. of the alert service bulletin.

Corrective Action

    (h) If any cracking is found during any inspection required by 
paragraph (g) of this AD, repair the cracking and repeat the 
inspection at the applicable compliance time specified in Table 1 of 
paragraph 1.E. ``Compliance'' of the alert service bulletin. Do the 
repair by doing all the applicable actions specified in the 
Accomplishment Instructions of the alert service bulletin.

[[Page 24576]]

Where the alert service bulletin specifies to report cracking to 
Boeing for repair instructions: Before further flight, repair any 
cracking according to a method approved by the Manager, Seattle 
Aircraft Certification Office (ACO), FAA; or using a method approved 
in accordance with paragraph (j)(3) of this AD.

Optional Terminating Action

    (i) Replacement of the doorstop fitting with a fitting made of 
7075 material having P/N 65-23674-7, in accordance with the 
Accomplishment Instructions of the alert service bulletin, 
terminates the repetitive inspections of that fitting, as required 
by paragraph (g) of this AD.

Alternative Methods of Compliance (AMOCs)

    (j)(1) The Manager, Seattle ACO, has the authority to approve 
AMOCs for this AD, if requested in accordance with the procedures 
found in 14 CFR 39.19.
    (2) The inspection methods specified in Figures 9 through 12 of 
the alert service bulletin, as required by paragraph (g) of this AD, 
at the thresholds and intervals specified in paragraph (g), are 
approved as a method of compliance (MOC) to paragraph (b) of AD 98-
11-03 and 98-11-03 R1, for the inspections of Structurally 
Significant Item F-16A, Supplemental Structural Inspection Document 
D6-48040-1, affected by the repair or modification. The MOC applies 
only to the areas inspected in accordance with Boeing Alert Service 
Bulletin 727-53A0228, dated March 24, 2005. All provisions of AD 98-
11-03 R1 that are not specifically referenced in this paragraph 
remain fully applicable and must be complied with.
    (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) Before using any AMOC approved in accordance with 14 CFR 
39.19 on any airplane to which the AMOC applies, notify the 
appropriate principal inspector in the FAA Flight Standards 
Certificate Holding District Office.

Material Incorporated by Reference

    (k) You must use Boeing Alert Service Bulletin 727-53A0228, 
dated March 24, 2005, 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. 06-3890 Filed 4-25-06; 8:45 am]
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